(19)
(11)EP 3 653 844 A1

(12)EUROPEAN PATENT APPLICATION

(43)Date of publication:
20.05.2020 Bulletin 2020/21

(21)Application number: 18206450.1

(22)Date of filing:  15.11.2018
(51)Int. Cl.: 
F01D 11/00  (2006.01)
F01D 5/22  (2006.01)
(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
Designated Extension States:
BA ME
Designated Validation States:
KH MA MD TN

(71)Applicant: Siemens Aktiengesellschaft
80333 München (DE)

(72)Inventors:
  • Overton, David
    Lincoln, LN4 1ST (GB)
  • Welburn, Peter
    Lincoln, LN6 7ES (GB)

(74)Representative: Maier, Daniel Oliver 
Siemens AG Postfach 22 16 34
80506 München
80506 München (DE)

  


(54)STRIP SEAL, ANNULAR SEGMENT AND METHOD FOR A GAS TURBINE


(57) The present invention relates to a strip seal (200) for use in a gas turbine, in particular for sealing the gap between adjacent turbine vane platforms (320), comprising an elongated main body (220) defining a longitudinal direction, the main body (220) comprising first and second ends (221, 222) delimiting the main body (220) along the longitudinal direction, and a cavity (240) defined by the main body (220). The strip seal (200) further comprises a locking member (260) projecting away from the main body (220) and may be resiliently deformed to be contained in said cavity (240). The strip seal (200) may be maintained in a linear track (362) being formed in a turbine vane platform (320) having a recess (366) for receiving said locking member (260). Thereby, assembly of the vane ring may be faster and more convenient and the strip seal (200) may be recovered in substantially undamaged condition.




Description


[0001] The present disclosure relates to a strip seal and an annular segment for a gas turbine. The present disclosure further relates to a method of assembling a gas turbine using the strip seal and the annular segment.

Background



[0002] Gas turbine engines, which are a specific example of turbomachines, generally include a rotor with a number of rows of rotor blades which are fixed to a rotor shaft via rotor discs and rows of stator vanes therebetween, which are fixed to the casing of the gas turbine. When a hot and pressurised working fluid flows through the rows of rotor blades and stator vanes in the main passage of a gas turbine, it transfers momentum to the rotor and thus imparts a rotary motion to the rotor while expanding and cooling. Maintaining the working fluid within the main passage is therefore crucial for engine performance as well as component life.

[0003] In certain known gas turbines, the rotor disc assemblies and/or stator vanes are assembled from a plurality of individual components, i.e. annular segments. However, assembling the individual components into an array causes gaps to be formed between adjacent segments. As such gaps may be utilised by the working fluid to escape from the main passage, it is known to provide seals, for example in the form of strip seals, to seal these gaps.

[0004] While it may be possible for some seals to be fitted during assembly of the annular segments, this may not be possible for certain strip seals. For such a purpose the arrayed segments define slots where they are interfaced. These slots are open-ended so that strip seals can be inserted following assembly of the segments. However, the strip seals may slide out of the open end of the slot. Assembly of segments may therefore be difficult and time consuming. Moreover, it may not be possible to ensure all strip seals are seated correctly.

[0005] Hence an alternative strip seal for a gas turbine, an alternative component of a gas turbine, and an alternative method of assembly of a gas turbine are highly desirable.

Summary



[0006] According to the present disclosure there is provided a strip seal, an annular segment and a method of assembling a gas turbine as set forth in the appended claims. Other features of the invention will be apparent from the dependent claims, and the description which follows.

[0007] Accordingly there may be provided a strip seal (200) for use in a gas turbine, comprising: an elongate main body (220) defining a longitudinal direction, the main body (220) comprising: a first end (221) and a second end (222) which delimit the main body (220) along the longitudinal direction, and a cavity (240) defined by the main body (220); and a locking member (260) which projects away from the main body (220); wherein the strip seal (260) is resiliently deformable to contain the locking member (260) in the cavity (240).

[0008] The strip seal (200) provides a sealing means which may be inserted into a slot formed by a pair of annular segments (300) and secured therein by means of the locking member (260) to maintain the strip seal (200) seated correctly.

[0009] The main body (220) may define: a central region (227) extending between the first end (221) and the second end (222), and a pair of equally-sized side regions (228, 229) flanking the central region (227); wherein the cavity (240) and the locking member (260) are located in one of the side regions (228, 229).

[0010] Where the central region (220) of the main body (100) is located in the gap between a pair of annular segments (300), the central region (220) seals the gap by virtue of its presence therein. By locating the cavity (240) and the locking member (260) in the side regions (130, 240), the central region (220) may better seal the gap.

[0011] The other one of the side regions (228, 229) may not be provided with a locking member (260).

[0012] A single locking member (260) may be sufficient for retaining the strip seal (200) in position. Moreover, the manufacturing of such a strip seal (200) and corresponding gas turbine annular segment (300) receiving the strip seal (200) may be improved. The locking member (260) may be configured to project from a cavity edge (242) of the main body (220), and the main body (220) and the locking member (260) are provided at an oblique angle to one another.

[0013] By providing the locking member (260) at an oblique angle relative to the main body (220), i.e. angling the locking member (260) towards one of the ends (221, 222), the strip seal (200) is provided in a retroserrate configuration which defines an insertion direction. On insertion of the strip seal (200) into a gas turbine assembly (300) in the insertion direction, the locking member (260) is caused to be depressed into the cavity (240). Assembly of the gas turbine may therefore be faster and more convenient.

[0014] The cavity (240) and the locking member (260) may be provided closer to the first end (221) than the second end (222) or closer to the second end (222) than the first end (221).

[0015] By locating the cavity (240) and the locking member (260) close to one of the ends (221, 222) of the main body (220), a visual indication is provided by means of which the ends (221, 222) become easily distinguishable. Thus the correct insertion of the strip seal (200) may be ensured, which may be particularly important where the strip seal (200) looks symmetrical to the eye but actually is intended to be inserted with a particular end (221, 222) first.

[0016] The cavity (240) may extend through the main body (220).

[0017] The strip seal (200) may be manufactured by suitable manufacturing processes, such as laser-cutting, of the cavity (240) into the strip seal (200) and deforming the strip seal (200) suitably so that the locking member (260) extends from the main body (220). This manufacturing process may be easier to carry out by cutting all the way through the strip seal (200) in order to form the cavity (240) and the locking member (260).

[0018] There may also be provided an annular segment (300) for a turbine rotor assembly or stator vane assembly of a gas turbine, comprising: a platform (320) having a leading end (321) and a trailing end (322) bounding the platform (320) along an axial direction; an aerofoil portion (340) extending from the platform (320) along a radial direction; a wedge face (360) provided between the leading end (321) and the trailing end (322); wherein the wedge face (360) defines: a linear track (362) extending along the wedge face (360), the linear track (362) having an open end (364); and a recess (366) formed along the linear track (362).

[0019] The annular segment (300) may be provided as a stator vane segment (300).

[0020] The linear track (362) may be formed in a radially outer platform (320) of the annular segment (300). The strip seal (200) according to the present disclosure is applicable particularly to the outer platforms (320) of stator vane segment (300).

[0021] The annular segment (300) may be provided as a rotor blade (300).

[0022] The linear track (362) may be formed in a radially inner platform (320) of the rotor blade (300). The strip seal (200) according to the present disclosure is also applicable to an assembly of blade-carrying rotor discs, particularly with reference to the radially inner platform (320).

[0023] There may also be provided an annular segment assembly (400) for a gas turbine, comprising: a strip seal (200) as set out above, and a first annular segment (300) and a second annular segment (300) as set out above; wherein a wedge face (360) of the first annular segment (300) and a wedge face (360) of the second annular segment (300) are interfaced so that: a gap (410) is defined between the wedge faces (360), a slot (430) is defined by a linear track (362) of the first annular segment (300) and a linear track (362) of the second annular segment (300); wherein the strip seal (200) is located in the slot (430), and the locking member (260) of the strip seal (200) is located in the recess (366) formed along the linear track (362) of the first annular segment (300) or the linear track (362) of the second annular segment (300).

[0024] There may also be provided a gas turbine comprising an annular segment assembly (400) as set out above.

[0025] There may also be provided a method of assembly of a gas turbine, comprising: forming an annular segment assembly (400) by: aligning a first annular segment (300) and a second annular segment (300) as set out above, thereby interfacing a wedge face (360) of the first annular segment (300) and a wedge face (360) of the second annular segment (300); sealing the gap (410) between the wedge faces (360) of the first annular segment (300) and the second annular segment (300) by: providing a strip seal (200) as set out above; inserting the strip seal (200) into a slot (430) formed by the component assembly (400), thereby causing the strip seal (200) to resiliently deform to locate the locking member (260) within the cavity (240); displacing the strip seal (200) along the slot (430) until the locking member (260) of the strip seal (200) reaches the recess (366), thus causing the locking member (260) to extend into the recess (366).

[0026] The method of assembly may comprise: separating the first annular segment (300) and the second annular segment (300), and recovering the strip seal (200) in a substantially undamaged condition. As part of assembly of a gas turbine it may be necessary to re-assemble some components, such as the rotor blade assemblies or the stator vane assemblies. According to the present method, the strip seal (200) is recoverable in a re-usable condition and can therefore be used following the disassembly of annular segments (300). Moreover, this is applicable also to service and maintenance of a gas turbine.

[0027] Conventional strip seals may not be seated correctly and may therefore suffer damage during assembly and/or disassembly of the annular assembly. Using the strip seal (200) according to the present disclosure allows the strip seals (100) to be recovered in a substantially undamaged condition.

Brief Description of the Drawings



[0028] Examples of the present disclosure will now be described with reference to the accompanying drawings, in which:

Figure 1 is a schematic representation of an example of a turbomachine;

Figure 2 shows an enlarged region of a section of a turbine of the turbomachine shown in Figure 1;

Figure 3 shows an end view of the rotor blades shown in Figure 1 and 2;

Figure 4 is a perspective view of a strip seal according to the present disclosure;

Figure 5 is view onto the strip seal of Figure 4;

Figure 6 is a perspective view of an annular segment according to the present disclosure;

Figure 7 is a partial perspective view of the annular segment of Figure 6; and

Figure 8 is a partial perspective view of a pair of annular segments of Figure 6 arrayed to form an annular assembly.


Detailed Description



[0029] The present disclosure relates to a strip seal for use in a turbomachine, such as a gas turbine, and a method of assembling a gas turbine provided with a strip seal.

[0030] By way of context, Figure 1 shows an example of a gas turbine engine in a sectional view, which illustrates the nature of components according to the present disclosure (for example rotor blades) and the environment in which they operate. The gas turbine engine comprises, in flow series, an inlet 62, a compressor section 64, a combustion section 66 and a turbine section 68, which are generally arranged in flow series and generally in the direction of a longitudinal or rotational axis 70. The gas turbine engine further comprises a shaft 72 which is rotatable about the rotational axis 70 and which extends longitudinally through the gas turbine engine. The rotational axis 70 is normally the rotational axis of an associated gas turbine engine. Hence any reference to "axial", "radial" and "circumferential" directions are with respect to the rotational axis 70.

[0031] The shaft 72 drivingly connects the turbine section 68 to the compressor section 64. In operation of the gas turbine engine, air 74, which is taken in through the air inlet 62 is compressed by the compressor section 64 and delivered to the combustion section or burner section 66. The burner section 66 comprises a burner plenum 76, one or more combustion chambers 78 defined by a double wall can 80 and at least one burner 82 fixed to each combustion chamber 78. The combustion chambers 78 and the burners 82 are located inside the burner plenum 76. The compressed air passing through the compressor section 64 enters a diffuser 84 and is discharged from the diffuser 84 into the burner plenum 76 from where a portion of the air enters the burner 82 and is mixed with a gaseous or liquid fuel. The air/fuel mixture is then burned and the combustion gas 86 or working gas from the combustion is channelled via a transition duct 88 to the turbine section 68.

[0032] The turbine section 68 may comprise a number of blade carrying discs 90 or turbine wheels attached to the shaft 72. In the example shown, the turbine section 68 comprises two discs 90 which each carry an annular array of turbine assemblies 12, which each comprises an aerofoil 14 embodied as a turbine blade 100. Turbine cascades 92 are disposed between the turbine blades 100. Each turbine cascade 92 carries an annular array of turbine assemblies 12, which each comprises an aerofoil 14 in the form of guiding vanes (i.e. stator vanes 96), which are fixed to a stator 94 of the gas turbine engine.

[0033] Figure 2 shows an enlarged view of a stator vane 96 and rotor blade 100. Arrows "A" indicate the direction of flow of combustion gas 86 past the aerofoils 96,100. Arrows "B" show air flow passages provided for sealing, and arrows "C" indicate cooling air flow paths for passing through the stator vanes 96. Cooling flow passages 101 may be provided in the rotor disc 90 which extend radially outwards to feed an air flow passage 103 in the rotor blade 100.

[0034] The combustion gas 86 from the combustion chamber 78 enters the turbine section 58 and drives the turbine blades 100 which in turn rotate the shaft 72 to drive the compressor. The guiding vanes 96 serve to optimise the angle of the combustion or working gas 86 on to the turbine blades.

[0035] Figure 3 shows a view of the rotor blades 100 looking upstream, facing the flow "A" shown in Figure 2.

[0036] Each rotor blade 100 comprises an aerofoil portion 104, a root portion 106 and a platform 108 from which the aerofoil extends.

[0037] The rotor blades 100 are fixed to the rotor disc 102 by means of their root portions 106, through which the flow passage 101 may extend. The root portions 106 have a shape that corresponds to notches (or grooves) 109 in the rotor disc 90, and are configured to prevent the rotor blade 100 from detaching from the rotor disc 102 in a radial direction as the rotor disc 102 spins.

[0038] A strip seal 110 is provided to seal a region (or gap) between pairs of adjacent platforms 108.

[0039] The segment of the present disclosure may relate to a rotor blade or another component for a gas turbine engine, for example a nozzle guide vane.

[0040] Figures 4 and 5 illustrate a strip seal 200 according to the present disclosure. Figure 4 is a perspective view of the strip seal 200, while Figure 5 is a top down view of the strip seal 200.

[0041] The strip seal 200 may be used with a gas turbine engine, such as the exemplary gas turbine engine of Figure 1. The strip seal 200 is a sealing member configured to seal an elongate gap, completely or at least partially, by means of its presence therein. More particularly, the strip seal 200 may be inserted into the turbine assemblies 12, i.e. the rotor blades 100 and/or the stator vanes 96, to seal gaps.

[0042] The strip seal 200 comprises a main body 220. The main body 220 has a generally elongate shape. In use, at least a portion of the main body 220 is physically located within a gap in order to seal said gap.

[0043] The main body 220 comprises a first end 221, a second end 222, and a pair of side edges 223, 224 extending between the first end 221 and the second end 222 of the main body 220. The first end 221 and the second end 222 bound the main body 220 along a first direction, e.g. longitudinal direction. The side edges 223, 224 bound the main body 220 along a second direction, e.g. lateral direction. The main body 220 further comprises a first surface 225 (or 'top face') and a second surface 226 (or bottom face'). The first surface 225 and the second surface 106 delimit the main body 220 along a third direction, which may be perpendicular to both the longitudinal direction and the lateral direction.

[0044] The main body 220 has a substantially constant cross-section along its length, i.e. from the first end 221 to the second end 222. According to the present example, the side edges 223, 224 are straight and arranged to be parallel. Moreover, the first surface 225 and the second surface 226 are flat and arranged to be parallel.

[0045] The main body 220 defines a central region 227 and a pair of side regions 228, 229, i.e. a 'centre' and two 'margins'. That is to say, the main body 220 may divided into geometric regions. The central regions 227 and the side regions 228, 229 extend from first end 221 to the second end 222. The side regions may be equally sized and arranged to flank the central region 227.

[0046] A cavity 240 is defined by the main body 220. The cavity 240 extends through the main body 220, i.e. from the first surface 225 to the second surface 226. According to the present example, the cavity 240 is a recess, for example a cut-out or notch, on one of the side edges 223, 224 of the main body 220.

[0047] The strip seal 200 comprises a locking member 260. The locking member 260 is carried by the main body 220 and configured to project away from the main body 220. More particularly, the locking member 260 is configured to project beyond at least one of the side edges 223, 224 or the surfaces 225, 226. That is to say, the locking member 260 extends from the main body 220 along a non-longitudinal direction. In other words, the locking member 260 extends at an angle to the longitudinal direction. According to some examples, the locking member 260 projects, i.e. extends, from one of the side edges 223, 224, while according to other examples the locking member 260 projects from one of the surfaces 225, 226. According to the present example, the locking member 260 extends from the first surface 225. More particularly, the locking member 260 extends from an edge 242 of the cavity 240.

[0048] The strip seal 200 is resiliently deformable to contain the locking member 260 in the cavity 240. That is to say, the strip seal 200, or at least a portion of the strip seal 200, is physically deformable so that the locking member 260 may be located within the cavity 240. Additionally, the strip seal 200 is configured to resist the locking member 260 being located in the cavity 240. That is to say, the locking member 260 is biased to assume a configuration in which the locking member 260 is not contained in, and therefore extends out of and away from, the cavity 240. According to the present example, the locking member 260 is resiliently deformable to be located in the cavity 240. Put another way, the locking member 260 may be resiliently biased such that at rest it is at an angle to the main body 220 of the strip seal 200, but may be forced, i.e. deformed, to take a position within the cavity 240.

[0049] The cavity 240 and the locking member 260 are located in one of the side regions 228, 229. Therefore, the cavity 240 and the locking member 260 are located beside the central region 227 extending along the strip seal 200, as opposed to being located within the central region 227. For example, the cavity 240 and the locking member 260 are provided at one of the side edges 223, 224 of the main body 220. By contrast, the central region 227 and the other side region 229 are provided without a locking member 260 extending therefrom. That is to say, the central region 227 and the other side region 229 are flat (or 'continuous').

[0050] The cavity 240 and the locking member 260 are provided towards the first end 221 or the second end 222 of the strip seal 200. According to other examples, the cavity 240 and the locking member 260 may not be provided at the first end 221 and the second end 222 of the strip seal 200. That is to say, the cavity 240 and locking member 260 may only be provided towards one of the first end 221 or the second end 222.

[0051] The strip seal 200 is provided in a retroserrate configuration. That is to say, the locking member 260 is angled towards the first end 221 or the second end 222 of the strip seal 200. Accordingly, the locking member 260 is configured to be depressed into the cavity 240 by means of being inserted in the insertion direction, and to resist removal along the opposite direction.

[0052] Figures 6 and 7 illustrate an annular segment 300 according to the present disclosure. Figure 6 shows a perspective view of the annular segment 300, while Figure 7 shows a partial perspective view of the annular segment 300. The annular segment 300 may be used with a gas turbine engine, such as the exemplary gas turbine engine of Figure 1. According to the present example, the annular segment 300 is provided as a turbine stator vane, for example a nozzle guide vane. In another example (not shown), the annular segment may be provided as a rotor blade, for example as shown in Figures 2, 3. Although the structure of a rotor blade and stator vane are different, they comprise common features as described in the following.

[0053] The annular segment 300 comprises a platform 320. The platform 320 has a leading end 321 which is spaced apart from a trailing end 322 along the axial direction. The leading end 321 and the trailing end 322 bound the platform 320 along the axial direction.

[0054] The annular segment 300 further comprises an aerofoil portion 340 extending from the platform 320 along the radial direction.

[0055] The annular segment 300 further comprises a pair of wedge faces 360 bounding the annular segment 300 along the circumferential direction. A wedge face 360 of the annular segment 300 is configured to be interfaced with a wedge face 360 of a corresponding annular segment 300 when arrayed to form an annular assembly, i.e. rotor blade or stator vane.

[0056] Each wedge face 360 defines a linear track 362 (or 'straight' track) extending along the wedge face 360. The linear track 362 is configured to receive the strip seal 200. More particularly, the linear track 362 may receive a side edge 223, 224 of the strip seal 200.

[0057] The linear track 362 comprises an open end 364. The annular segment 300 is configured to receive the strip seal 200 through the open end 364. Suitably, the open end 364 is accessible along the axial direction and/or the radial direction. In particular, the open end 364 remains accessible when the annular segments 300 have been arrayed (i.e. assembled to form an array) to form an annular assembly a gas turbine, i.e. a stator vane assembly or a rotor blade assembly. According to some examples, the linear track 362 is formed in radially inwards from the aerofoil portion 340, e.g. the root of the annular segment 300. According to the present example, the linear track 362 is formed radially outwards from the aerofoil portion 340, in the outer platform of the nozzle guide vane.

[0058] At least one of the wedge faces 360 defines a recess 366 formed along the linear track 362. According to some examples, both wedge faces 360 define a recess 366 each along the linear track 362. According to the present example, one of the wedge faces 360 defines a recess 366. Suitably, one recess 366 may in use suffice to retain the locking feature 260 of the strip seal 200 and, thus, the strip seal 200 as a whole. That is to say, the recess 366 is configured to receive the locking member 260 of the strip seal 200 so that the locking member 260 may bend away from the main body 220, e.g. as shown in Figure 4.

[0059] The recess 366 defines a section of the linear track 362 which an increased cross section. The recess 366 may be provided so as to increase the depth of the linear track 360, measured along the circumferential direction. The recess 366 may be provided so as to increase the width of the linear track 360, measured along the axial and/or radial direction. According to the present example, the recess 366 is provided to expand the linear track 360 in the axial direction and the radial direction. Put another way, the recess 366 is an enlarged region of the track 360 for receiving the locking member 260.

[0060] Figure 8 is a partial perspective view of an annular assembly 400 of gas turbine. According to the example illustrated in Figure 6, two annular segments 300 are arrayed to define the annular assembly 400, e.g. a partial stator vane.

[0061] The two annular segments 300 have been arranged next to one another so that a wedge face 360 of the first annular segment 300 and a corresponding wedge face 360 of the second annular segment 300 are interfaced.

[0062] A gap 410 is formed between the interfaced wedge faces 360 of the annular segments 300. The strip seal 200 is configured to seal the gap 410 such that, in use, air is inhibited from passing through the gap. Suitably, the strip seal 200 is inserted into an opening 420 in an outer face of the (sub-)assembly 400. The opening 420 is formed from the open ends 364 of the linear tracks 362 in the annular segments 300. Moreover, the linear tracks 362 co-operate to define a slot 430 extending into the assembly 400.

[0063] As the strip seal 200 is inserted, with the first end 221 being inserted first, the locking member 260 is depressed by at least one of the annular segments 300. That is to say, insertion of the strip seal 200 causes a mechanical deformation of the strip seal 200, in that the locking member 260 is forced into the cavity 240 formed by the strip seal 200.

[0064] As the strip seal 200 is inserted farther into the slot 420, the locking member 260 remains in the cavity 240 until the locking member 260 reaches the recess 226. The strip seal 260 then assumes its previous configuration, i.e. the locking member 260 extends from the main body 220 and into the recess 226.

[0065] During disassembly of the disc annular assembly 400, the strip seal 200 may be recovered. Whilst the locking member 260 prevents the strip seal 200 from sliding out of the slot 430 through the opening 420, the strip seal 200 is removable from the annular segments 300 once these have been separated. Moreover, the strip seal 200 may be recoverable in a substantially undamaged condition and re-useable.

[0066] The example shown in Figure 8 is a stator vane assembly, although it will be understood sealing may be achieved in the same way between blade platforms of a rotor blade assembly.

[0067] Attention is directed to all papers and documents which are filed concurrently with or previous to this specification in connection with this application and which are open to public inspection with this specification, and the contents of all such papers and documents are incorporated herein by reference.

[0068] All of the features disclosed in this specification (including any accompanying claims, abstract and drawings), and/or all of the steps of any method or process so disclosed, may be combined in any combination, except combinations where at least some of such features and/or steps are mutually exclusive.

[0069] Each feature disclosed in this specification (including any accompanying claims, abstract and drawings) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. Thus, unless expressly stated otherwise, each feature disclosed is one example only of a generic series of equivalent or similar features.

[0070] The invention is not restricted to the details of the foregoing embodiment(s). The invention extends to any novel one, or any novel combination, of the features disclosed in this specification (including any accompanying claims, abstract and drawings), or to any novel one, or any novel combination, of the steps of any method or process so disclosed.


Claims

1. A strip seal (200) for use in a gas turbine, comprising:

an elongate main body (220) defining a longitudinal direction, the main body (220) comprising:

a first end (221) and a second end (222) which delimit the main body (220) along the longitudinal direction, and

a cavity (240) defined by the main body (220); and

a locking member (260) which projects away from the main body (220);

wherein the strip seal (260) is resiliently deformable to contain the locking member (260) in the cavity (240).


 
2. The strip seal (200) according to claim 1, wherein
the main body (220) defines:

a central region (227) extending between the first end (221) and the second end (222), and

a pair of equally-sized side regions (228, 229) flanking the central region (227);

wherein the cavity (240) and the locking member (260) are located in one of the side regions (228, 229).
 
3. The strip seal (200) according to claim 2, wherein the other one of the side regions (228, 229) is not provided with a locking member (260).
 
4. The strip seal (200) according to any one of claims 1 to 3, wherein
the locking member (260) is configured to project from a cavity edge (242) of the main body (220), and the main body (220) and the locking member (260) are provided at an oblique angle to one another.
 
5. The strip seal (200) according to any one of claims 2 to 4, wherein
the cavity (240) and the locking member (260) are provided closer to the first end (221) than the second end (222) or closer to the second end (222) than the first end (221).
 
6. The strip seal (200) according to any preceding claim, wherein
the cavity (240) extends through the main body (220).
 
7. An annular segment (300) for a turbine rotor assembly or stator vane assembly of a gas turbine, comprising:

a platform (320) having a leading end (321) and a trailing end (322) bounding the platform (320) along an axial direction;

an aerofoil portion (340) extending from the platform (320) along a radial direction;

a wedge face (360) provided between the leading end (321) and the trailing end (322);

wherein the wedge face (360) defines:

a linear track (362) extending along the wedge face (360), the linear track (362) having an open end (364); and

a recess (366) formed along the linear track (362).


 
8. The annular segment (300) according to claim 7, wherein the annular segment (300) is provided as a stator vane segment (300).
 
9. The annular segment (300) according to claim 8, wherein the linear track (362) is formed in a radially outer platform (320) of the annular segment (300).
 
10. The annular segment (300) according to claim 7, wherein the annular segment (300) is provided as a rotor blade (300).
 
11. The annular segment (300) according to claim 10, wherein the linear track (362) is formed in a radially inner platform (320) of the rotor blade (300).
 
12. An annular segment assembly (400) for a gas turbine, comprising:

a strip seal (200) according to any one of claims 1 to 6, and

a first annular segment (300) and a second annular segment (300) according to any one of claims 7 to 11;

wherein a wedge face (360) of the first annular segment (300) and a wedge face (360) of the second annular segment (300) are interfaced so that:

a gap (410) is defined between the wedge faces (360),

a slot (430) is defined by a linear track (362) of the first annular segment (300) and a linear track (362) of the second annular segment (300);

wherein the strip seal (200) is located in the slot (430), and

the locking member (260) of the strip seal (200) is located in the recess (366) formed along the linear track (362) of the first annular segment (300) or the linear track (362) of the second annular segment (300).


 
13. A gas turbine comprising an annular segment assembly (400) according to claim 12.
 
14. A method of assembly of a gas turbine, comprising:

forming an annular segment assembly (400) by:

aligning a first annular segment (300) and a second annular segment (300) according to any one of claims 7 to 11, thereby interfacing a wedge face (360) of the first annular segment (300) and a wedge face (360) of the second annular segment (300);

sealing the gap (410) between the wedge faces (360) of the first annular segment (300) and the second annular segment (300) by:

providing a strip seal (200) according to any one of claims 1 to 6;

inserting the strip seal (200) into a slot (430) formed by the component assembly (400), thereby causing the strip seal (200) to resiliently deform to locate the locking member (260) within the cavity (240);

displacing the strip seal (200) along the slot (430) until the locking member (260) of the strip seal (200) reaches the recess (366), thus causing the locking member (260) to extend into the recess (366).


 
15. The method of assembly of a gas turbine, comprising:

separating the first annular segment (300) and the second annular segment (300), and

recovering the strip seal (200) in a substantially undamaged condition.


 




Drawing