(19)
(11)EP 3 287 603 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
26.06.2019 Bulletin 2019/26

(21)Application number: 17180864.5

(22)Date of filing:  12.07.2017
(51)International Patent Classification (IPC): 
F01D 9/04(2006.01)
F01D 25/24(2006.01)

(54)

CHAMFERED STATOR VANE RAIL

ABGESCHRÄGTE LEITSCHAUFELSCHIENE

RAIL D'AUBE DE STATOR CHANFREINÉ


(84)Designated Contracting States:
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

(30)Priority: 25.08.2016 US 201615246875

(43)Date of publication of application:
28.02.2018 Bulletin 2018/09

(73)Proprietor: United Technologies Corporation
Farmington, CT 06032 (US)

(72)Inventors:
  • PROPHETER-HINCKLEY, Tracy A.
    Manchester, CT 06042 (US)
  • GATES, Roger
    West Hartford, CT 06107 (US)
  • GRIFFIN, David Richard
    Tolland, CT 06084 (US)
  • AUXIER, James Tilsley
    Bloomfield, CT 06002 (US)

(74)Representative: Dehns 
St. Brides House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)


(56)References cited: : 
EP-A2- 1 039 096
EP-A2- 2 369 139
US-A1- 2006 045 745
US-A1- 2013 209 248
EP-A2- 1 384 858
US-A- 6 164 656
US-A1- 2012 128 465
US-A1- 2016 169 037
  
      
    Note: Within nine months from the publication of the mention of the grant of the European patent, any person may give notice to the European Patent Office of opposition to the European patent granted. Notice of opposition shall be filed in a written reasoned statement. It shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention).


    Description

    FIELD



    [0001] The present disclosure relates to gas turbine engines, and more specifically, to a chamfered stator vane rail for gas turbine engines.

    BACKGROUND



    [0002] Gas turbine engines typically include at least a compressor section to pressurize inflowing air, a combustor section to burn a fuel in the presence of the pressurized air, and a turbine section to extract energy from the resulting combustion gases. One or more sections of the gas turbine engine may include a plurality of vane assemblies having vanes interspersed between rotor assemblies that carry the blades of successive stages of the section. Gas turbine engines may have various secondary airflow streams to provide cooling air to gas turbine engine components including stator vane assemblies and/or rotor assemblies. Losses in delivery of cooling air may have a negative effect on engine fuel burn, performance/efficiency, and component durability.

    [0003] US 6,164,656 A discloses an interface seal for a turbine engine.

    [0004] EP 1 039 096 A2 discloses a turbine nozzle including a plurality of vanes joined at opposite ends to inner and outer bands.

    [0005] US 2016/169037 A1 discloses a shroud sealing arrangement for a gas turbine engine.

    [0006] US 2012/128465 A1 discloses a steam turbine diaphragm stage having a self-aligning flow splitter.

    [0007] US 2006/045745 A1 discloses a simplified vane mounting arrangement.

    [0008] EP 1 384 88 A2 discloses a low pressure turbine casing having a conical annular shell circumscribed about a centerline.

    [0009] US 2013/209248 A1 discloses a stator assembly for a gas turbine engine.

    [0010] EP 2 369 139 A2 discloses a gas turbine engine with the features of the preamble of claim 1.

    SUMMARY



    [0011] From a first aspect, the invention provides a gas turbine engine as claimed in claim 1.

    [0012] In various embodiments, the chamfered face of the stator vane rail may comprise a substantially flat surface. In various embodiments, the chamfered face of the stator vane rail may comprise a curved surface extending in a radial direction away from the axis. In various embodiments, the chamfered face of the stator vane rail may be oriented at an angle of about 45° to about °60 relative to the axis. In various embodiments, the chamfered face of the stator vane rail may be oriented at an angle of about 15° to about 45° relative to the axis. In various embodiments, the chamfered face may comprise a bow tied surface. In various embodiments, the chamfered face may comprise a sinusoidal surface.

    [0013] In various embodiments, the ID stator vane platform of the stator vane assembly may comprise an ID forward rail and an ID aft rail located axially opposite the ID forward rail. The ID aft rail may comprise an ID axis defining a perpendicular direction from the ID aft rail. The ID aft rail may comprise an ID leading face and an ID trailing face located axially opposite the ID leading face. The ID aft rail may comprise an ID chamfered face extending from the ID leading face, wherein the ID chamfered face comprises a radially inner surface of the ID aft rail, and wherein the ID chamfered face is oriented at an angle of about 45° to about 60° relative to the ID axis. In various embodiments, the OD chamfered face of the OD stator vane rail may comprise a curved surface extending in a radial direction away from the OD axis. In various embodiments, the OD chamfered face of the OD stator vane rail may be oriented at an angle of about 45° to about °60 relative to the OD axis. In various embodiments, the OD chamfered face may comprise a bow tied surface. In various embodiments, the OD chamfered face may comprise a sinusoidal surface.

    [0014] In various embodiments, the OD chamfered face of the OD stator vane platform may comprise a curved surface extending in a radial direction away from the OD axis. In various embodiments, the OD chamfered face of the OD stator vane platform may be oriented at an angle of about 45° to about °60 relative to the OD axis. In various embodiments, the OD chamfered face may comprise a bow tied surface. In various embodiments, the gas turbine engine may further comprise an OD leading face seal located forward the OD leading face. In various embodiments, the gas turbine engine may further comprise an OD trailing face seal located aft the OD trailing face.

    [0015] The forgoing features and elements may be combined in various combinations without exclusivity, unless expressly indicated herein otherwise. These features and elements as well as the operation of the disclosed embodiments will become more apparent in light of the following description and accompanying drawings.

    BRIEF DESCRIPTION OF THE DRAWINGS



    [0016] The subject matter of the present disclosure is particularly pointed out and distinctly claimed in the concluding portion of the specification. A more complete understanding of the present disclosure, however, may best be obtained by referring to the detailed description and claims when considered in connection with the following illustrative figures. In the following figures, like reference numbers refer to similar elements and steps throughout the figures.

    FIG. 1 illustrates a cross-section view of a gas turbine engine, in accordance with various embodiments;

    FIG. 2 illustrates a cross-section view of a high pressure turbine section of a gas turbine engine comprising a chamfered stator vane rail, in accordance with various embodiments;

    FIG. 3A illustrates a cross-section view of a high pressure turbine section of a gas turbine engine comprising a chamfered stator vane rail having a curved surface, in accordance with various embodiments;

    FIG. 3B illustrates a cross-section view of a high pressure turbine section of a gas turbine engine comprising a chamfered stator vane rail having a sinusoidal surface, in accordance with various embodiments;

    FIG. 3C illustrates a front cross-section view of a chamfered stator vane rail having a bow tied surface, in accordance with various embodiments;

    FIG. 4 illustrates a cross-section view of a high pressure turbine section of a gas turbine engine further comprising a feather seal, in accordance with various embodiments; and

    FIG. 5 illustrates a cross-section view of a high pressure turbine section of a gas turbine engine further comprising an ID chamfered stator vane rail, in accordance with various embodiments.



    [0017] Elements and steps in the figures are illustrated for simplicity and clarity and have not necessarily been rendered according to any particular sequence. For example, steps that may be performed concurrently or in different order are illustrated in the figures to help to improve understanding of embodiments of the present disclosure.

    DETAILED DESCRIPTION



    [0018] The detailed description of exemplary embodiments herein makes reference to the accompanying drawings, which show exemplary embodiments by way of illustration. While these exemplary embodiments are described in sufficient detail to enable those skilled in the art to practice the disclosures, it should be understood that other embodiments may be realized and that logical changes and adaptations in design and construction may be made in accordance with this disclosure and the teachings herein. Thus, the detailed description herein is presented for purposes of illustration only and not of limitation.

    [0019] The scope of the disclosure is defined by the appended claims and their legal equivalents rather than by merely the examples described. For example, the steps recited in any of the method or process descriptions may be executed in any order and are not necessarily limited to the order presented. Furthermore, any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step. Also, any reference to attached, fixed, coupled, connected or the like may include permanent, removable, temporary, partial, full and/or any other possible attachment option. Additionally, any reference to without contact (or similar phrases) may also include reduced contact or minimal contact. Surface shading lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.

    [0020] As used herein, "aft" refers to the direction associated with a tail (e.g., the back end) of an aircraft, or generally, to the direction of exhaust of a gas turbine engine. As used herein, "forward" refers to the direction associated with a nose (e.g., the front end) of the aircraft, or generally, to the direction of flight or motion.

    [0021] In various embodiments, and with reference to FIG. 1, a gas turbine engine 120 is disclosed. Gas turbine engine 120 may comprise a two-spool turbofan that generally incorporates a fan section 122, a compressor section 124, a combustor section 126, and a turbine section 128. Gas turbine engine 120 may also comprise, for example, an augmenter section, and/or any other suitable system, section, or feature. In operation, fan section 122 may drive air along a bypass flow-path B, while compressor section 124 may further drive air along a core flow-path C for compression and communication into combustor section 126, before expansion through turbine section 128. FIG. 1 provides a general understanding of the sections in a gas turbine engine, and is not intended to limit the disclosure. The present disclosure may extend to all types of applications and to all types of turbine engines, including, for example, turbojets, turboshafts, and three spool (plus fan) turbofans wherein an intermediate spool includes an intermediate pressure compressor ("IPC") between a low pressure compressor ("LPC") and a high pressure compressor ("HPC"), and an intermediate pressure turbine ("IPT") between the high pressure turbine ("HPT") and the low pressure turbine ("LPT").

    [0022] In various embodiments, gas turbine engine 120 may comprise a low speed spool 130 and a high speed spool 132 mounted for rotation about an engine central longitudinal axis A-A' relative to an engine static structure 136 via one or more bearing systems 138 (shown as, for example, bearing system 138-1 and bearing system 138-2 in FIG. 1). It should be understood that various bearing systems 138 at various locations may alternatively or additionally be provided, including, for example, bearing system 138, bearing system 138-1, and/or bearing system 138-2.

    [0023] In various embodiments, low speed spool 130 may comprise an inner shaft 140 that interconnects a fan 142, a low pressure (or a first) compressor section 144, and a low pressure (or a second) turbine section 146. Inner shaft 140 may be connected to fan 142 through a geared architecture 148 that can drive fan 142 at a lower speed than low speed spool 130. Geared architecture 148 may comprise a gear assembly 160 enclosed within a gear housing 162. Gear assembly 160 may couple inner shaft 140 to a rotating fan structure. High speed spool 132 may comprise an outer shaft 150 that interconnects a high pressure compressor ("HPC") 152 (e.g., a second compressor section) and high pressure (or a first) turbine section 154. A combustor 156 may be located between HPC 152 and high pressure turbine 154. A mid-turbine frame 157 of engine static structure 136 may be located generally between high pressure turbine 154 and low pressure turbine 146. Mid-turbine frame 157 may support one or more bearing systems 138 in turbine section 128. Inner shaft 140 and outer shaft 150 may be concentric and may rotate via bearing systems 138 about engine central longitudinal axis A-A'. As used herein, a "high pressure" compressor and/or turbine may experience a higher pressure than a corresponding "low pressure" compressor and/or turbine.

    [0024] In various embodiments, the air along core airflow C may be compressed by low pressure compressor 144 and HPC 152, mixed and burned with fuel in combustor 156, and expanded over high pressure turbine 154 and low pressure turbine 146. Mid-turbine frame 157 may comprise airfoils 159 located in core airflow path C. Low pressure turbine 146 and high pressure turbine 154 may rotationally drive low speed spool 130 and high speed spool 132, respectively, in response to the expansion.

    [0025] In various embodiments, and with reference to FIG. 2, a section of high pressure turbine 154 of FIG. 1 is depicted in greater detail. High pressure turbine 154 comprises a stator vane assembly 201. Stator vane assembly 201 comprises a stator vane 205 configured to direct airflow through high pressure turbine 154. Stator vane 205 is coupled at a first end to inner diameter (ID) stator vane rail 210 and at a second end to outer diameter (OD) stator vane rail 220. In various embodiments, stator vane 205 may be the first forward stator vane located in high pressure turbine 154. ID stator vane rail 210 may be radially spaced apart from OD stator vane rail 220. In various embodiments, OD stator vane rail 220 may form a portion of an outer core engine structure, and ID stator vane rail 210 may form a portion of an inner core engine structure to at least partially define an annular core gas flow path through high pressure turbine 154. In various embodiments, stator vane assembly 201 may comprise multiple components wherein ID stator vane rail 210 and OD stator vane rail 220 are coupled to stator vane 205 to form stator vane assembly 201. In various embodiments, stator vane assembly 201 may comprise a single component wherein stator vane 205, ID stator vane rail 210, and OD stator vane rail 220 may also comprise a single casting. In various embodiments, stator vane 205, ID stator vane rail 210, and OD stator vane rail 220 may comprise any suitable material, such as, for example, an age-hardenable, nickel-based superalloy.

    [0026] In various embodiments, ID stator vane rail 210 may comprise an inner platform 211, an ID forward rail 213 and an ID aft rail 215. Inner platform 211 may be configured to couple ID stator vane rail 210 to stator vane 205. ID forward rail 213 may be located forward of ID aft rail 215. ID forward rail 213 and ID aft rail 215 may be configured to direct an ID cooling airflow to provide cooling air to ID engine components (such as, for example, blade outer air seals (BOAS), vane supports, seals, cases, and/or the like). OD stator vane rail 220 comprises an outer platform 221, an OD forward rail 225 and an OD aft rail 230. Outer platform 221 is configured to couple OD stator vane rail 220 to stator vane 205. OD forward rail 225 is located forward of OD aft rail 230. OD forward rail 225 comprises a forward rail aperture 228 configured to allow a cooling airflow.

    [0027] High pressure turbine 154 also comprises an OD flow rail 207. OD flow rail 207 is configured to direct a cooling airflow along the outer diameter of high pressure turbine 154. In that regard, OD flow rail 207 and OD stator vane rail 220 define a secondary airflow path 209 to allow cooling air to flow through high pressure turbine 154 and cool OD engine components (such as, for example, an OD BOAS). The cooling air flows through secondary airflow path 209 by passing through forward rail aperture 228, through a vane support aperture 208 in OD flow rail 207, and over OD aft rail 230.

    [0028] OD aft rail 230 comprises a leading edge 232 and a trailing edge 237. Leading edge 232 comprises an axially forward surface of OD aft rail 230 and trailing edge 237 comprises an axially aft surface of OD aft rail 230, axially opposite of leading edge 232. According to the invention OD aft rail 230 is configured to reduce recirculation of cooling air in secondary airflow path 209, and improve efficiency of cooling air provided to OD engine components (such as, for example, an OD BOAS). Reducing the recirculation of cooling air by OD aft rail 230 mitigates thermal stress issues caused by the cooling air from secondary airflow path 209 impinging on OD aft rail 230. OD aft rail 230 also improves airflow through secondary airflow path 209, enabling a cooling airflow having a higher pressure and cooler temperature. For example, and in various embodiments, OD aft rail 230 may provide at least a 5% to 10% increase in pressure to the cooling airflow along secondary airflow path 209.

    [0029] In that regard, according to the invention OD aft rail 230 comprises a chamfered edge 234 configured to direct cooling air over the OD aft rail 230 and to OD engine components. Chamfered edge 234 enables the cooling air to flow over OD aft rail 230 with minor interruption and/or impingement. Chamfered edge 234 comprises a forward portion of a radially outer surface of OD aft rail 230, located between leading edge 232 and trailing edge 237. Chamfered edge 234 may be formed using any suitable technique. For example, OD aft rail 230 may be machined to form chamfered edge 234. In various embodiments, OD aft rail 230 may also be cast, additively manufactured, and/or the like to comprise chamfered edge 234.

    [0030] In various embodiments, chamfered edge 234 may be oriented at an angle relative to an axis 290. Axis 290 may be oriented substantially parallel to engine central longitudinal axis A-A', and perpendicular relative to leading edge 232, from which chamfered edge 234 is oriented radially away from. In that regard, and in various embodiments, chamfered edge 234 may be oriented at a chamfered edge angle delta ("δ") relative to axis 290. Chamfered edge angle δ may be about 15° to about 60°, about 15° to about 45°, or about 45° to about 60° (wherein about in this context means +/- 1°). Chamfered edge angle δ may also comprise any other angle suitable to reduce cooling air recirculation and improve efficiency of cooling air provided to OD engine components.

    [0031] In various embodiments, chamfered edge 234 may comprise any suitable shape capable of reducing cooling air recirculation and/or improving efficiency of cooling air provided to OD engine components. For example, chamfered edge 234 may comprise a substantially flat surface. In various embodiments, with reference to FIG. 3A, OD aft rail 330 may also comprise a chamfered edge 334-1 having a curved surface. In that regard, chamfered edge 334-1 may comprise a convex shape extending outward from engine central longitudinal axis A-A', such as, for example, a filleted surface, an oval surface, and/or the like. In various embodiments, chamfered edge 334-1 may also comprise a convex shape protruding inwards (in the y direction) with regard to engine central longitudinal axis A-A' (with brief reference to FIG. 2).

    [0032] In various embodiments, and with reference to FIG. 3B, chamfered edge 334-2 may also comprise a sinusoidal surface. In that regard, the sinusoidal surface of chamfered edge 334-2 may comprise a sinusoidal shape varying in depth (varying positive and negative in the y direction) when moving forward and aft in the x direction across OD aft rail 330.

    [0033] In various embodiments, and with reference to FIG. 3C, chamfered edge 334-3 may also comprise a bow tied surface (or a compound surface). In various embodiments, the bow tied surface of chamfered edge 334-3 may be configured to account for rotation of OD aft rail 330 and/or OD stator vane rail 320 during gas turbine engine operation. In that regard, the bow tied surface of chamfered edge 334-3 may comprise variable depths (varying positive and negative in the y direction) when moving forward and aft in both the z direction and the x direction across OD aft rail 330. The bow tied surface may therefore comprise a compound surface having variable depths (varying positive and negative in the y direction) across multiple directions (in both the z direction and the x direction).

    [0034] In various embodiments, and with reference again to FIG. 2, high pressure turbine 154 may also comprise a feather seal slot 240. Feather seal slot 240 may comprise a partial trench located on an axial surface of OD aft rail 230 between leading edge 232 and trailing edge 237. In various embodiments, feather seal slot 240 may comprise a partial trench machined into OD aft rail 230. In various embodiments, OD aft rail 230 may also be cast, additively manufactured, and/or the like to comprise feather seal slot 240. Feather seal slot 240 may comprise any shape and size suitable to fit a feather seal (e.g., feather seal 445, with brief reference to FIG. 4), such as, for example, a rectangular shape.

    [0035] In various embodiments, high pressure turbine 154 may also comprise an OD leading edge seal 250 and an OD trailing edge seal 255. In various embodiments, OD leading edge seal 250 may be configured to provide an improved airflow seal between OD flow rail 207 and OD aft rail 230 to reduce airflow leakage. In that regard, OD leading edge seal 250 may be disposed within an OD forward annular cavity 251 adjacent to and aft of OD flow rail 207 and forward of OD aft rail 230. OD leading edge seal 250 may form a "W" shape, and/or any other suitable shape, and may be biased outwardly from engine central longitudinal axis A-A'. The "W" shape may also enable OD leading edge seal 250 to compress when placed into OD forward annular cavity 251, further improving the seal and reducing airflow leakage. OD leading edge seal 250 may comprise any suitable material capable of sealing and/or minimizing airflow leakage, such as, for example, a nickel alloy or a nickel chromium alloy.

    [0036] In various embodiments, OD trailing edge seal 255 may be configured to provide an improved airflow seal aft of OD aft rail 230 to reduce airflow leakage. In that regard, OD trailing edge seal 255 may be located aft of OD aft rail 230 and disposed within an OD aft annular cavity 256. OD trailing edge seal 255 may form a "W" shape, and/or any other suitable shape, and may be biased inwardly towards engine central longitudinal axis A-A'. The "W" shape may also enable OD trailing edge seal 255 to compress when placed into OD aft annular cavity 256, further improving the seal and reducing airflow leakage. OD trailing edge seal 255 may comprise any suitable material capable of sealing and/or minimizing airflow leakage, such as, for example, a nickel alloy or a nickel chromium alloy.

    [0037] In various embodiments, and with reference to FIG. 4, high pressure turbine 454 may also comprise a feather seal 445. Feather seal 445 may be configured to further minimize air flow leakage in secondary airflow path 209 (with brief reference to FIG. 2). For example, and in various embodiments, feather seal 445 may be located in feather seal slot 240. The use of feather seal 445 in feather seal slot 240 may further minimize air flow leakage in the axial direction (with reference to engine central longitudinal axis A-A'). Feather seal 445 may comprise any shape, size, and material suitable to minimize air flow leakage. For example, feather seal 445 may comprise a small flat metal object, machined to size to fit within feather seal slot 240.

    [0038] In various embodiments, and with reference to FIG. 5, a stator vane assembly 501 having an ID stator vane rail 510 is disclosed. ID stator vane rail 510 may comprise an inner platform 511, a ID forward rail 513, and an ID aft rail 515. ID forward rail 513 may comprise an ID forward rail aperture 514 configured to provide a cooling airflow to ID engine components. ID aft rail 515 may be similar to OD aft rail 230, and may comprise similar airflow benefits and characteristics.

    [0039] In various embodiments, ID aft rail 515 may comprise an ID leading edge 562 axially forward an ID trailing edge 567. ID leading edge 562 may comprise an axially forward surface of ID aft rail 515 and ID trailing edge 567 may comprise an axially aft surface of ID aft rail 515, axially opposite of ID leading edge 562. In various embodiments, ID aft rail 515 may also comprise an ID feather seal slot 560 located between ID leading edge 562 and ID trailing edge 567. ID leading edge 562 may comprise an ID chamfered edge 564 configured to direct cooling air aft of ID aft rail 515 and to ID engine components. Chamfered edge 234 may enable a cooling air to flow over ID aft rail 515 without interruption and/or impingement. ID chamfered edge 564 may comprise a forward portion of a radially inner surface of ID aft rail 515, located between ID leading edge 562 and ID trailing edge 567.

    [0040] In various embodiments, ID chamfered edge 564 may be formed using any suitable technique. For example, ID aft rail 515 may be machined to form ID chamfered edge 564. In various embodiments, ID aft rail 515 may also be cast, additively manufactured, and/or the like to comprise ID chamfered edge 564. In various embodiments, ID chamfered edge 564 may be oriented at an angle relative to an ID axis 595. ID axis 595 may be oriented substantially parallel to engine central longitudinal axis A-A', and perpendicular to ID leading edge 562, from which ID chamfered edge 564 is oriented radially away from. In that regard, and in various embodiments, ID chamfered edge 564 may be oriented at an ID chamfered edge angle gamma ("γ") relative to ID axis 595. ID chamfered edge angle γ may be about 15° to about 60°, about 15° to about 45°, or about 45° to about 60° (wherein about in this context means +/- 1°). ID chamfered edge angle γ may also comprise any other angle suitable to reduce cooling air recirculation and improve efficiency of cooling air provided to ID engine components.

    [0041] In various embodiments, ID chamfered edge 564 may comprise any suitable shape capable of reducing cooling air recirculation and/or improving efficiency of cooling air provided to ID engine components. For example, ID chamfered edge 564 may comprise a substantially flat surface. In various embodiments, ID aft rail 515 may also comprise an ID chamfered edge 564 having a curved surface, such as a convex shape or a concave shape. In various embodiments, ID chamfered edge 564 may also comprise a filleted surface, an oval surface, a sinusoidal surface, and/or the like. In various embodiments ID chamfered edge 564 may also comprise a bow tied surface. In that regard, the bow tied surface of ID chamfered edge 564 may comprise variable depths and heights over the circumferential and axial length of ID aft rail 515. In various embodiments, the bow tied surface of ID chamfered edge 564 may be configured to account for rotation of ID aft rail 515 and/or ID stator vane rail 510 during gas turbine engine operation.

    [0042] Benefits, other advantages, and solutions to problems have been described herein with regard to specific embodiments. Furthermore, the connecting lines shown in the various figures contained herein are intended to represent exemplary functional relationships and/or physical couplings between the various elements. It should be noted that many alternative or additional functional relationships or physical connections may be present in a practical system. However, the benefits, advantages, solutions to problems, and any elements that may cause any benefit, advantage, or solution to occur or become more pronounced are not to be construed as critical, required, or essential features or elements of the disclosures. The scope of the disclosures is accordingly to be limited by nothing other than the appended claims and their legal equivalents, in which reference to an element in the singular is not intended to mean "one and only one" unless explicitly so stated, but rather "one or more." Moreover, where a phrase similar to "at least one of A, B, or C" is used in the claims, it is intended that the phrase be interpreted to mean that A alone may be present in an embodiment, B alone may be present in an embodiment, C alone may be present in an embodiment, or that any combination of the elements A, B and C may be present in a single embodiment; for example, A and B, A and C, B and C, or A and B and C.

    [0043] Systems, methods and apparatus are provided herein. In the detailed description herein, references to "various embodiments", "one embodiment", "an embodiment", "an example embodiment", etc., indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.

    [0044] Furthermore, no element, component, or method step in the present disclosure is intended to be dedicated to the public regardless of whether the element, component, or method step is explicitly recited in the claims. As used herein, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.


    Claims

    1. A gas turbine engine (120), comprising:

    a turbine section (154);

    an OD flow rail (207); and

    a stator vane assembly (201) in the turbine section (154), the stator vane assembly (201) comprising:

    a stator vane (205) having a first end opposite a second end;

    an ID stator vane platform (210) coupled to the first end;

    an OD stator vane platform (220) coupled to the second end, wherein the OD stator vane platform (220) comprises:

    an OD forward rail (225) extending radially from the stator vane platform (220); and

    an OD aft rail (230) extending radially from the stator vane platform (220) and located axially opposite and aft of the OD forward rail (225), wherein the OD aft rail (230) comprises:

    an OD axis (290) defining a perpendicular direction relative to the OD aft rail (230);

    an OD leading face (232); and

    an OD trailing face (237) located axially opposite the OD leading face (232),

    wherein the OD flow rail (207) and the OD vane platform (220) define a secondary airflow path, such that in use, cooling air flows through the secondary airflow path by passing through an aperture (228) in the OD forward rail (225), through an aperture (208) in the flow rail (207) and over the OD aft rail (230),

    characterised in that the OD aft rail (230) comprises an OD chamfered face (234) extending from the OD leading face (232), wherein the OD chamfered face (234) comprises a radially outer surface of the aft rail (230) such that, in use, cooling air flows over the OD aft rail (230) with minor interruption and/or impingement.


     
    2. The gas turbine engine (120) of claim 1, wherein the chamfered face (234) comprises a substantially flat surface.
     
    3. The gas turbine engine (120) of claim 1, wherein the chamfered face (234) comprises a curved surface.
     
    4. The gas turbine engine (120) of claim 3, wherein the curved surface extends in a radial direction away from the axis.
     
    5. The gas turbine engine (120) of claim 1, wherein the chamfered face (234) is oriented at an angle of about 45° to about °60 relative to the axis (290).
     
    6. The gas turbine engine (120) of claim 1, wherein the chamfered face (234) is oriented at an angle of about 15° to about 45° relative to the axis (290).
     
    7. The gas turbine engine (120) of claim 1, wherein the chamfered face (234) comprises a bow tied surface.
     
    8. The gas turbine engine (120) of claim 7, wherein the chamfered face (234) comprises a sinusoidal surface.
     
    9. The gas turbine engine (120) of any preceding claim, wherein the ID stator vane platform (510) comprises:

    an ID forward rail (513); and

    an ID aft rail (515) located axially opposite the ID forward rail (513), wherein the ID aft rail (515) comprises:

    an ID axis defining a perpendicular direction relative to the ID aft rail (515);

    an ID leading face (562);

    an ID trailing face (567) located axially opposite the ID leading face (562);

    an ID chamfered face (564) extending from the ID leading face (562), wherein

    the ID chamfered face (564) comprises a radially inner surface of the ID aft rail (515), and wherein the ID chamfered face (564) is oriented at an angle of about 45° to about 60° relative to the ID axis.


     
    10. The gas turbine engine (120) of any preceding claim, further comprising an OD leading face seal (250) located forward the OD leading face (232).
     
    11. The gas turbine engine (120) of any preceding claim, further comprising an OD trailing face seal (255) located aft the OD trailing face (237).
     


    Ansprüche

    1. Gasturbinentriebwerk (120), Folgendes umfassend:

    einen Turbinenabschnitt (154);

    eine OD-Strömungsschiene (207); und

    eine Leitschaufelanordnung (201) in dem Turbinenabschnitt (154), wobei die Leitschaufelanordnung (201) Folgendes umfasst:

    eine Leitschaufel (205) mit einem ersten Ende und einem gegenüberliegenden zweiten Ende;

    eine ID-Leitschaufelplattform (210), die mit dem ersten Ende gekoppelt ist;

    eine OD-Leitschaufelplattform (220), die mit dem zweiten Ende gekoppelt ist, wobei die OD-Leitschaufelplattform (220) Folgendes umfasst:

    eine vordere OD-Schiene (225), die sich radial von der Leitschaufelplattform (220) erstreckt; und

    eine hintere OD-Schiene (230), die sich radial von der Leitschaufelplattform (220) erstreckt und sich hinter der vorderen OD-Schiene (225) und dieser axial gegenüber befindet, wobei die hintere OD-Schiene (230) Folgendes umfasst:

    eine OD-Achse (290), die eine senkrechte Richtung in Bezug auf die hintere OD-Schiene (230) definiert;

    eine OD-Vorderseite (232); und

    eine OD-Hinterseite (237), die sich der OD-Vorderseite (232) axial gegenüber befindet,

    wobei die OD-Strömungsschiene (207) und die OD-Schaufelplattform (220) einen sekundären Luftströmungspfad derart definieren, dass bei Verwendung Kühlungsluft durch Durchlaufen einer Öffnung (228) durch den sekundären Luftströmungspfad in die vordere OD-Schiene (225), durch eine Öffnung (208) in die Strömungsschiene (207) und über die hintere OD-Schiene (230) strömt,

    dadurch gekennzeichnet, dass die hintere OD-Schiene (230) eine abgeschrägte OD-Seite (234) umfasst, die sich von der OD-Vorderseite (232) erstreckt, wobei die abgeschrägte OD-Seite (234) eine radial äußere Fläche der hinteren Schiene (230) derart umfasst, dass bei Verwendung Kühlungsluft über die hintere OD-Schiene (230) mit geringfügiger Unterbrechung und/oder geringfügigem Aufprall strömt.


     
    2. Gasturbinentriebwerk (120) nach Anspruch 1, wobei die abgeschrägte Seite (234) eine im Wesentlichen ebene Fläche umfasst.
     
    3. Gasturbinentriebwerk (120) nach Anspruch 1, wobei die abgeschrägte Seite (234) eine gekrümmte Fläche umfasst.
     
    4. Gasturbinentriebwerk (120) nach Anspruch 3, wobei die gekrümmte Fläche sich in einer radialen Richtung von der Achse weg erstreckt.
     
    5. Gasturbinentriebwerk (120) nach Anspruch 1, wobei die abgeschrägte Seite (234) in Bezug auf die Achse (290) in einem Winkel von etwa 45° bis etwa 60° ausgerichtet ist.
     
    6. Gasturbinentriebwerk (120) nach Anspruch 1, wobei die abgeschrägte Seite (234) in Bezug auf die Achse (290) in einem Winkel von etwa 15° bis etwa 45° ausgerichtet ist.
     
    7. Gasturbinentriebwerk (120) nach Anspruch 1, wobei die abgeschrägte Seite (234) eine bogengebundene Fläche umfasst.
     
    8. Gasturbinentriebwerk (120) nach Anspruch 7, wobei die abgeschrägte Seite (234) eine sinusförmige Fläche umfasst.
     
    9. Gasturbinentriebwerk (120) nach einem der vorstehenden Ansprüche, wobei die ID-Leitschaufelplattform (510) Folgendes umfasst:

    eine vordere ID-Schiene (513); und

    eine hintere ID-Schiene (515), die sich axial gegenüber der vorderen ID-Schiene (513) befindet, wobei die hintere ID-Schiene (515) Folgendes umfasst:

    eine ID-Achse, die eine senkrechte Richtung in Bezug auf die hintere ID-Schiene (515) definiert;

    eine ID-Vorderseite (562);

    eine ID-Hinterseite (567), die sich axial gegenüber der ID-Vorderseite (562) befindet;

    eine abgeschrägte ID-Seite (564), die sich von der ID-Vorderseite (562) erstreckt, wobei die abgeschrägte ID-Seite (564) eine radial innere Fläche der hinteren ID-Schiene (515) umfasst, und wobei die abgeschrägte ID-Seite (564) in Bezug auf die ID-Achse in einem Winkel von etwa 45° bis etwa 60° ausgerichtet ist.


     
    10. Gasturbinentriebwerk (120) nach einem der vorstehenden Ansprüche, ferner eine OD-Vorderseitendichtung (250) umfassend, die sich vor der OD-Vorderseite (232) befindet.
     
    11. Gasturbinentriebwerk (120) nach einem der vorstehenden Ansprüche, ferner eine OD-Hinterseitendichtung (255) umfassend, die sich hinter der OD-Hinterseite (237) befindet.
     


    Revendications

    1. Moteur à turbine à gaz (120), comprenant :

    une section de turbine (154) ;

    un rail d'écoulement OD (diamètre extérieur) (207) ; et

    un ensemble d'aube de stator (201) dans la section de turbine (154), l'ensemble d'aube de stator (201) comprenant :

    une aube de stator (205) ayant une première extrémité opposée à une seconde extrémité ;

    une plateforme d'aube de stator ID (diamètre intérieur) (210) couplée à la première extrémité ;

    une plateforme d'aube de stator OD (220) couplée à la seconde extrémité, dans lequel la plateforme d'aube de stator OD (220) comprend :

    un rail avant OD (225) s'étendant radialement à partir de la plateforme d'aube de stator (220) ; et

    un rail arrière OD (230) s'étendant radialement à partir de la plateforme d'aube de stator (220) et situé axialement à l'opposé et à l'arrière du rail avant OD (225), dans lequel le rail arrière OD (230) comprend :

    un axe OD (290) définissant une direction perpendiculaire par rapport au rail arrière OD (230) ;

    une face d'attaque OD (232) ; et

    une face de fuite OD (237) située axialement à l'opposé de la face d'attaque OD (232) ;

    dans lequel le rail d'écoulement OD (207) et la plateforme d'aube OD (220) définissent un trajet d'écoulement d'air secondaire, de sorte qu'en cours d'utilisation, l'air de refroidissement s'écoule à travers le trajet d'écoulement d'air secondaire en passant à travers une ouverture (228) dans le rail avant OD (225), à travers une ouverture (208) dans le rail d'écoulement (207) et sur le rail arrière OD (230),

    caractérisé en ce que le rail arrière OD (230) comprend une face chanfreinée OD (234) s'étendant à partir de la face d'attaque OD (232), dans lequel la face chanfreinée OD (234) comprend une surface radialement extérieure du rail arrière (230) de sorte qu'en cours d'utilisation, l'air de refroidissement s'écoule sur le rail arrière OD (230) avec une interruption et/ou une incidence mineures.


     
    2. Moteur à turbine à gaz (120) selon la revendication 1, dans lequel la face chanfreinée (234) comprend une surface sensiblement plane.
     
    3. Moteur à turbine à gaz (120) selon la revendication 1, dans lequel la face chanfreinée (234) comprend une surface incurvée.
     
    4. Moteur à turbine à gaz (120) selon la revendication 3, dans lequel la surface incurvée s'étend dans une direction radiale s'éloignant de l'axe.
     
    5. Moteur à turbine à gaz (120) selon la revendication 1, dans lequel la face chanfreinée (234) est orientée à un angle d'environ 45° à environ 60° par rapport à l'axe (290).
     
    6. Moteur à turbine à gaz (120) selon la revendication 1, dans lequel la face chanfreinée (234) est orientée à un angle d'environ 15° à environ 45° par rapport à l'axe (290).
     
    7. Moteur à turbine à gaz (120) selon la revendication 1, dans lequel la face chanfreinée (234) comprend une surface en forme de noeud papillon.
     
    8. Moteur à turbine à gaz (120) selon la revendication 7, dans lequel la face chanfreinée (234) comprend une surface sinusoïdale.
     
    9. Moteur à turbine à gaz (120) selon une quelconque revendication précédente, dans lequel la plateforme d'aube de stator ID (510) comprend :

    un rail avant ID (513) ; et

    un rail arrière ID (515) situé axialement à l'opposé du rail avant ID (513), dans lequel le rail arrière ID (515) comprend :

    un axe ID définissant une direction perpendiculaire par rapport au rail arrière ID (515) ;

    une face d'attaque ID (562) ;

    une face de fuite ID (567) située axialement à l'opposé de la face d'attaque ID (562) ;

    une face chanfreinée ID (564) s'étendant à partir de la face d'attaque ID (562), dans lequel

    la face chanfreinée ID (564) comprend une surface radialement intérieure du rail arrière ID (515), et dans lequel la face chanfreinée ID (564) est orientée à un angle d'environ 45° à environ 60° par rapport à l'axe ID.


     
    10. Moteur à turbine à gaz (120) selon une quelconque revendication précédente, comprenant en outre un joint de face d'attaque OD (250) situé à l'avant de la face d'attaque OD (232) .
     
    11. Moteur à turbine à gaz (120) selon une quelconque revendication précédente, comprenant en outre un joint de face de fuite OD (255) situé à l'arrière de la face de fuite OD (237) .
     




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    Cited references

    REFERENCES CITED IN THE DESCRIPTION



    This list of references cited by the applicant is for the reader's convenience only. It does not form part of the European patent document. Even though great care has been taken in compiling the references, errors or omissions cannot be excluded and the EPO disclaims all liability in this regard.

    Patent documents cited in the description