(19)
(11)EP 2 875 226 B1

(12)EUROPEAN PATENT SPECIFICATION

(45)Mention of the grant of the patent:
29.04.2020 Bulletin 2020/18

(21)Application number: 13819314.9

(22)Date of filing:  18.07.2013
(51)International Patent Classification (IPC): 
F02C 7/28(2006.01)
F01D 11/00(2006.01)
F02C 7/32(2006.01)
(86)International application number:
PCT/US2013/051083
(87)International publication number:
WO 2014/015142 (23.01.2014 Gazette  2014/04)

(54)

BAYONETED ANTI-ROTATION TURBINE SEALS

BAJONETTIERTE DREHVERHINDERNDE TURBINENDICHTUNGEN

JOINTS DE TURBINE ANTI-ROTATION À BAÏONNETTE


(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: 18.07.2012 US 201213551818

(43)Date of publication of application:
27.05.2015 Bulletin 2015/22

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

(72)Inventors:
  • BURT, Jonathan P.
    Sturbridge, Massachusetts 01566 (US)
  • SANDOVAL, Jonathan Perry
    Hebron, CT 06248 (US)

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


(56)References cited: : 
EP-A1- 1 277 917
US-A1- 2005 175 459
US-A1- 2012 027 598
US-A1- 2012 177 495
US-A- 6 106 234
US-A1- 2010 215 501
US-A1- 2012 177 485
US-A1- 2012 177 495
  
      
    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

    TECHNICAL FIELD



    [0001] This invention relates to disks for gas turbine engines and particularly to coverplates that fit adjacent the recesses in the disks to provide a cooling path there between.

    BACKGROUND OF THE INVENTION



    [0002] Early coverplates were used as windage covers disposed upon rotating gas turbine engine disks. More modern coverplates are also used to attain a cooling of the disk. An axial extension of the cover may extend into a broach area of a turbine disk (or rotor) radially outside the disk rim and radially supported by the blade. The coverplate is spaced radially from the disk to provide a dead ended annular space. Cooler air migrates to this space and insulates the disk rim from the engine's extremely hot working medium that is acting on the turbine blades. Tests have shown that this feature reduces the disk rim temperature by over 37.8°C (100°F), which increases the disk low cycle fatigue life and allows the use of less expensive material from which the disk is fabricated.

    [0003] An assembly having the features of the preamble of claim 1 is disclosed in EP 1277917 A1.

    SUMMARY



    [0004] According to a first aspect, the invention provides an assembly for connecting a coverplate to a first rotor as set forth in claim 1.

    [0005] The invention also provides a method of assembling a coverplate and a first rotor, as set forth in claim 7.

    [0006] Embodiments of the disclosure are set forth in the dependent claims.

    BRIEF DESCRIPTION OF THE DRAWINGS



    [0007] The various features and advantages of the disclosed examples will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows.

    Figure 1 shows a gas turbine engine, including non-limiting embodiment of the invention.

    Figure 2 is a side view of a turbine section of the engine of Figure 1.

    Figure 3 is a perspective, aft view of a rotor along the line 3-3 of Figure 2.

    Figure 4A is a perspective view, taken along the lines 4-4 of Figure 2 of an aft coverplate for use with forward rotor.

    Figure 4B is a side view of the aft coverplate taken along the lines 4B-4B of Figure 4A.

    Figure 5 is a depiction of an assembly of the forward rotor and the aft coverplate associated with the forward rotor of Figure 2.

    Figure 6A is a side view taken along lines 6-6 of Figure 6B.

    Figure 6B is a perspective view of the coverplate of Figure 6A.

    Figure 7A, is a perspective view taken of a combination of a sleeve, an aft coverplate and the aft rotor as shown in Figure 2.

    Figure 7B, is a perspective side views taken of a combination of a sleeve, an aft coverplate and the aft rotor as shown in Figure 2.

    Figure 7B, is a perspective side views taken of a combination of a sleeve, an aft coverplate and the aft rotor as shown in Figure 2.

    Figure 7C, is a perspective view, partially in section, taken of a combination of a sleeve, an aft coverplate and the aft rotor taken along the lines 7C-7C of Figure 7A.


    DETAILED DESCRIPTION



    [0008] Referring to Figure 1, a gas turbine engine 10 includes a fan section 15, a compressor section 20, a combustor 25 and a turbine section 30. The example compressor section 20 includes a low pressure compressor section 35 and a high pressure compressor section 40. The turbine section 30 includes a high pressure turbine 45 and a low pressure turbine 50. The high pressure compressor section 40 and the high pressure turbine 45 are supported by a high spool 55. The low pressure compressor section 35 and low pressure turbine 50 are supported on a low spool 60. Spools 55 and 60 and their attached components rotate about a main axis A. Air drawn in through the compressor section 20 is compressed and fed into the combustor 25. In the combustor 25, the compressed air is mixed with fuel and ignited to generate a high speed gas stream. This gas stream is drives the turbine section 30.

    [0009] Referring now to Figure 2, a depiction of a turbine assembly 45 is shown. One of ordinary skill in the art will recognize that the teachings of this invention may be used for either the high pressure turbine assembly 40 or the low pressure turbine assembly 45. Moreover, one of ordinary skill will recognize that the teachings herein can be used wherever rotors or blades need to be cooled and may include other parts of the engine like the high pressure compressor section 40, more turbine stages or other types of engines besides the gas turbine engine 10 shown herein.

    [0010] Referring again to Figure 2, a rotor assembly includes a forward rotor 65, an aft rotor 70. A forward rotor forward coverplate 75 defines a space 77 between the forward rotor forward coverplate 75 and the forward rotor 65; a forward rotor aft coverplate 80 defines a space 83 between the forward rotor aft coverplate 80 and the forward rotor 65; and, an aft rotor forward coverplate 85 defines a space 87 between the aft rotor forward coverplate 85 and the aft rotor 70. An aft rotor aft coverplate 90 defines a space 91 between the aft rotor aft coverplate 90 and the aft rotor 70. The aft rotor 70 has axially extending teeth 93 that extend forward therefrom. A sleeve 94 attaches to an aft side 96 of the aft rotor 70 as will be discussed herein.

    [0011] Referring now to Figure 3, a perspective aft view of a forward rotor 65 is shown. The forward rotor 65 has a body 95 that has a plurality of radially extending teeth 100 (shown generically) that holds blades (not shown) as is known in the art. The forward rotor 65 has an aft hub 105 that has a plurality of aft tabs 110. The aft tabs 110 each have a forward surface 113 for engaging the aft rotor aft coverplate 90 as will be discussed herein. An area 120 between the aft tabs 110 and the body 95 receives the teeth 93 of the aft rotor 70, forward tabs 110 and the aft coverplate 80 as will be discussed herein.

    [0012] Referring to Figure 4A and 4B, a side view and a perspective view of the forward rotor 65 aft coverplate 80 is shown. Coverplate 80 has a body 163, a forward surface 165, cogs 185 and central opening 187. Passageways 190 are formed between adjacent cogs which extend radially inwardly. Each passageway 190 has an angled surface 191 that extends radially outwardly and axially aft from the forward surface 165 to the aft surface 195. The cogs 185 have a flat surface 200 that pushes against the forward surface 113 of the aft tabs 110 on the forward rotor 65. The coverplate 80 has an area 205 axially forward and radially inward of each cog 85, which is a thickened (or reinforced), to withstand any torque placed on the coverplate.

    [0013] Referring now to Figure 5, an assembly 206 of the aft coverplate 80, the forward rotor 65, and the aft rotor 70 is shown. The aft coverplate 80 is inserted through slots 120 between aft tabs 110. The coverplate 80 is then rotated circumferentially about the aft hub 105 so that the cogs 185 are disposed in register and axially aligned with forward surface 113 and the flat surface 200 is contacting the forward surface of aft tabs 110. Axially extending teeth 93 from the aft rotor 70 are then pushed into gaps 113 to lock the coverplate 80 axially forward the aft tabs 110 (see Also Figure 2). The aft coverplate 80 may not now move circumferentially because of the interaction of the teeth 93 extending between the cogs 185 nor may it move axially because the disposition of the cogs 185 axially forward and in register with forward surface 113 of aft tabs 110. The teeth 93 act as a lock to lock the cogs 185 axially forward and in register with forward surface 113 of aft tabs 110. The aft coverplate 80 (like all coverplates described herein) is flexible such that as the coverplates are installed, they flex to allow the sealing surfaces 180 to seal against the forward rotor 65.

    [0014] Referring now to Figures 6A and 6B, a side and a perspective view of the aft rotor 70 aft cover 90 is shown. The aft rotor 70 aft cover 90 has a body 210, a forward side 215, an aft side 220. A plurality of bayonet tabs 240 extends from a radially inner portion 242 and an axially aft portion 243 of the aft rotor aft cover 90. One of ordinary skill in the art will notice that the forward rotor 65 forward coverplate 75 is constructed and interacts with the forward rotor 65 in the same manner as the aft rotor aft coverplate 90 does with the aft rotor 70 though tabs 266 in the forward coverplate 75 are disposed behind tabs 267 in the forward rotor 65.

    [0015] Referring now to Figures 7A - 7C, the aft rotor 70 is shown in conjunction with the aft rotor aft coverplate 90 and sleeve 94. Similar in construction to the forward hub 125 of the forward rotor 65, the aft rotor 65 has an aft hub 246. A plurality of aft tabs 241 extend radially outwardly from the aft hub 246. The aft tabs have a forward surface 243 for engaging the aft rotor aft coverplate 90 as will be discussed herein.

    [0016] The sleeve 94 has a plurality of sprockets 245 that extend axially forward from end 250 of the sleeve 94. Gaps 246 extend between the sprockets 245.

    [0017] Referring now to Figures 7B and 7C, an assembly 260 that includes the sleeve 94, the aft rotor 70 and the aft rotor aft coverplate 90 is shown. The bayonet tabs 240 of the aft coverplate 90 are inserted from aft through gaps 247. The coverplate 90 is then rotated circumferentially about the aft hub 246 so that the bayonet tabs 240 of the aft rotor 70 are disposed behind, axially aligned with each other and in contact with the forward surface 243 of the aft tabs 241 extending from the aft hub 246. Because, the bayonet tabs 240 are no longer in the gaps 247, the sprockets 245 are then inserted in the gaps 247 to lock the bayonet tabs 240 forward of the aft tabs 241. The aft coverplate 90 may not now move circumferentially nor may it move axially because the bayonet tabs 240 of the aft rotor 70 are disposed axially forward and in contact with the forward surface 243 of the aft tabs 241. The sprockets 245 act as a lock to lock the bayonet tabs 240 axially forward and in register with forward surface 243 of the aft tabs 241.

    [0018] By using the assemblies 206, 260, a part such as a coverplate 80 or 90 may be attached to a rotor 65, 70 with a single assembly that performs another function. For instance assembly 206, which includes the aft coverplate 80, the forward rotor 65, and the aft rotor 70, acts to drive torque. Similarly, the assembly 260, which includes the sleeve 94, the aft rotor 70 and the aft rotor aft coverplate 90, acts as a heat shield and a spacer. No parts are added with the sole function of locking the rotor and the part together. Each portion of the assembly performs more than one function in the engine 100 than locking the coverplate 80 or 90 to the rotor 65 or 70.

    [0019] The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from this disclosure. The scope of legal protection given to this disclosure can only be determined by studying the following claims.


    Claims

    1. An assembly for connecting a coverplate (80) to a first rotor (65), said assembly comprising:

    a first rotor (65) for use in a rotating gas turbine engine (10) and configured to hold blades;

    a second rotor (70) for use in a rotating gas turbine engine (10);

    a coverplate (80) mounted to said first rotor (65); and

    a lock assembly preventing said coverplate (80) from rotating circumferentially or moving axially away from said first rotor (65),

    wherein said lock assembly comprises:

    a first tab (110) mounted to said first rotor (65),

    a cog (185) mounted to said coverplate (80), said cog (185) being axially aligned with said first tab (110); and

    a tooth (93) preventing said first tab (110) and said cog (185) from being unaligned with each other;

    said tooth (93) is attached to said second rotor (70), characterised in that

    said lock assembly is also configured to drive torque between said first rotor (65) and said second rotor (70), and said second rotor (70) is configured to hold blades.


     
    2. The assembly of claim 1, wherein said first tab (110) is axially aft said cog (185).
     
    3. The assembly of claim 1, wherein said cog (185) is axially aft said first tab (110).
     
    4. The assembly of any of claims 1 to 3, wherein said coverplate (80) has a reinforced area adjacent said cog (185), said reinforced area for minimizing torque effects on said coverplate (80).
     
    5. The assembly of any preceding claim, wherein the coverplate (80) is urged against said first rotor (65) when said first tab (110) is disposed axially behind said cog (185).
     
    6. The assembly of any preceding claim, wherein said coverplate (80) has a passageway (190) between adjacent cogs (185) thereof, said passageway (190) having an angled surface (191) that extends radially outwardly and axially aft from the forward surface (165) of the coverplate (80) to an aft surface (195) of said coverplate (80).
     
    7. A method of assembling a coverplate (80) and a first rotor (65) comprising the steps of:

    providing a first rotor (65) for use in a rotating gas turbine engine (10) and configured to hold blades, said first rotor (65) having a first plurality of tabs (110) mounted thereto, said first tabs (110) having a first gap disposed between each adjacent first tab (110);

    providing a second rotor (70) for use in a rotating gas turbine engine (10);

    providing a coverplate (80) having a plurality of cogs (185) mounted thereto, said cogs (185) having a second gap disposed between each adjacent cog (185);

    maneuvering said first tabs (110) through said second gaps or said cogs (185) through said first gaps;

    rotating said coverplate (80) relative to said first rotor (65) to align said first tabs (110) and said cogs (185) axially;

    filling said first gap or said second gap with a tooth (93) attached to said second rotor (70), such that said first tabs (110) may not rotate circumferentially relative to said cogs (185), may not move axially away from said first rotor (65), and characterised in that torque is driven between the first rotor (65) and second rotor (70), and in that the second rotor (70) is configured to hold blades.


     


    Ansprüche

    1. Baugruppe zum Verbinden einer Abdeckplatte (80) mit einem ersten Rotor (65), wobei die Baugruppe Folgendes umfasst:

    einen ersten Rotor (65) zur Verwendung in einem rotierenden Gasturbinenmotor (10) und konfiguriert, um Schaufeln zu halten;

    einen zweiten Rotor (70) zur Verwendung in einem rotierenden Gasturbinenmotor (10);

    eine Abdeckplatte (80), die an dem ersten Rotor (65) montiert ist; und

    eine Verriegelungsbaugruppe, die verhindert, dass sich die Abdeckplatte (80) umlaufend dreht oder axial weg von dem ersten Rotor (65) bewegt,

    wobei die Verriegelungsbaugruppe Folgendes umfasst:

    eine erste Lasche (110), die an dem ersten Rotor (65) montiert ist,

    ein Rädchen (185), das an der Abdeckplatte (80) montiert ist,

    wobei das Rädchen (185) axial auf die erste Lasche (110) ausgerichtet ist; und

    einen Zahn (93), der verhindert, dass die erste Lasche (110) und das Rädchen (185) nicht aufeinander ausgerichtet sind;

    wobei der Zahn (93) an dem zweiten Rotor (70) angebracht ist,

    dadurch gekennzeichnet, dass

    die Verriegelungsbaugruppe auch konfiguriert ist, um Drehmoment zwischen dem ersten Rotor (65) und dem zweiten Rotor (70) anzutreiben, und der zweite Rotor (70) konfiguriert ist, um Schaufeln zu halten.


     
    2. Baugruppe nach Anspruch 1, wobei sich die erste Lasche (110) axial hinter dem Rädchen (185) befindet.
     
    3. Baugruppe nach Anspruch 1, wobei sich das Rädchen (185) axial hinter der ersten Lasche (110) befindet.
     
    4. Baugruppe nach einem der Ansprüche 1 bis 3, wobei die Abdeckplatte (80) einen verstärkten Bereich benachbart zu dem Rädchen (185) aufweist, wobei der verstärkte Bereich dazu dient, Drehmomentauswirkungen auf die Abdeckplatte (80) zu minimieren.
     
    5. Baugruppe nach einem vorhergehenden Anspruch, wobei die Abdeckplatte (80) gegen den ersten Rotor (65) gedrängt wird, wenn die erste Lasche (110) axial hinter dem Rädchen (185) angeordnet ist.
     
    6. Anordnung nach einem der vorstehenden Ansprüche, wobei die Deckplatte (80) einen Durchgang (190) zwischen angrenzenden Zähnen (185) davon aufweist, wobei der Durchgang (190) eine abgewinkelte Fläche (191) aufweist, die radial nach außen und axial nach hinten von der vorderen Fläche (165) der Deckplatte (80) zu einer hinteren Fläche (195) der Deckplatte (80) verläuft.
     
    7. Verfahren zum Zusammenbauen einer Abdeckplatte (80) und eines ersten Rotors (65), die folgenden Schritte umfassend:

    Bereitstellen eines ersten Rotors (65) zur Verwendung in einem rotierenden Gasturbinenmotor (10) und konfiguriert, um Schaufeln zu halten, wobei der erste Rotor (65) eine erste Vielzahl von daran montierten Laschen (110) aufweist, wobei die ersten Laschen (110) eine erste Lücke aufweisen, die zwischen jeder benachbarten ersten Lasche (110) angeordnet ist;

    Bereitstellen eines zweiten Rotors (70) zur Verwendung in einem rotierenden Gasturbinenmotor (10);

    Bereitstellen einer Abdeckplatte (80), die eine Vielzahl von daran montierten Rädchen (185) aufweist, wobei die Rädchen (185) eine zweite Lücke aufweisen, die zwischen jedem benachbarten Rädchen (185) angeordnet ist;

    Manövrieren der ersten Laschen (110) durch die zweiten Lücken oder die Rädchen (185) durch die ersten Lücken;

    Drehen der Abdeckplatte (80) relativ zu dem ersten Rotor (65), um die ersten Laschen (110) und die Rädchen (185) axial auszurichten;

    Füllen der ersten Lücke oder der zweiten Lücke mit einem Zahn (93), der an dem zweiten Rotor (70) angebracht ist, sodass sich die ersten Laschen (110) nicht umlaufend relativ zu den Rädchen (185) drehen können, sich nicht axial weg von dem ersten Rotor (65) bewegen können, und dadurch gekennzeichnet,

    dass Drehmoment zwischen dem ersten Rotor (65) und dem zweiten Rotor (70) angetrieben wird, und dass der zweite Rotor (70) konfiguriert ist, um Schaufeln zu halten.


     


    Revendications

    1. Ensemble permettant de raccorder une plaque de recouvrement (80) à un premier rotor (65), ledit ensemble comprenant :

    un premier rotor (65) destiné à être utilisé dans un moteur à turbine à gaz rotatif (10) et configuré pour maintenir des aubes ;

    un second rotor (70) destiné à être utilisé dans un moteur à turbine à gaz rotatif (10) ;

    une plaque de recouvrement (80) montée sur ledit premier rotor (65) ; et

    un ensemble de verrouillage empêchant ladite plaque de recouvrement (80) de tourner de manière circonférentielle ou de se déplacer axialement à l'écart dudit premier rotor (65),

    dans lequel ledit ensemble de verrouillage comprend :

    une première patte (110) montée sur ledit premier rotor (65), un rouage (185) monté sur ladite plaque de recouvrement (80),

    ledit rouage (185) étant aligné axialement avec ladite première patte (110) ; et

    une dent (93) empêchant ladite première patte (110) et ledit rouage (185) de ne pas être alignés l'une avec l'autre ;

    ladite dent (93) est fixée audit second rotor (70),

    caractérisé en ce que ledit ensemble de verrouillage est également configuré pour entraîner un couple entre ledit premier rotor (65) et ledit second rotor (70), et ledit second rotor (70) est configuré pour maintenir des aubes.


     
    2. Ensemble selon la revendication 1, dans lequel ladite première patte (110) est axialement en arrière dudit rouage (185) .
     
    3. Ensemble selon la revendication 1, dans lequel ledit rouage (185) est axialement en arrière de ladite première patte (110).
     
    4. Ensemble selon l'une quelconque des revendications 1 à 3, dans lequel ladite plaque de recouvrement (80) a une zone renforcée adjacente audit rouage (185), ladite zone renforcée permettant de minimiser les effets de couple sur ladite plaque de recouvrement (80).
     
    5. Ensemble selon une quelconque revendication précédente, dans lequel la plaque de recouvrement (80) est poussée contre ledit premier rotor (65) lorsque ladite première patte (110) est disposée axialement derrière ledit rouage (185).
     
    6. Ensemble selon une quelconque revendication précédente, dans lequel ladite plaque de couverture (80) présente un passage (190) entre les rouages adjacents (185) de celle-ci, ledit passage (190) ayant une surface inclinée (191) qui s'étend radialement vers l'extérieur et axialement à l'arrière de la surface avant (165) de la plaque de couverture (80) à une surface arrière (195) de ladite plaque de couverture (80).
     
    7. Procédé d'assemblage d'une plaque de recouvrement (80) et d'un premier rotor (65) comprenant les étapes :

    de fourniture d'un premier rotor (65) destiné à être utilisé dans un moteur à turbine à gaz rotatif (10) et configuré pour maintenir des aubes, ledit premier rotor (65) ayant une première pluralité de pattes (110) montées dessus, lesdites premières pattes (110) ayant un premier espace disposé entre chaque première patte adjacente (110) ;

    de fourniture d'un second rotor (70) destiné à être utilisé dans un moteur à turbine à gaz rotatif (10) ;

    de fourniture d'une plaque de recouvrement (80) sur laquelle sont montés une pluralité de rouages (185), lesdits rouages (185) ayant un second espace disposé entre chaque rouage adjacent (185) ;

    de manÅ“uvre desdites premières pattes (110) à travers lesdits seconds espaces ou desdits rouages (185) à travers lesdits premiers espaces ;

    de rotation de ladite plaque de recouvrement (80) par rapport audit premier rotor (65) pour aligner lesdites premières pattes (110) et lesdits rouages (185) axialement ;

    de remplissage dudit premier espace ou dudit second espace avec une dent (93) fixée audit second rotor (70), de sorte que lesdites premières pattes (110) ne peuvent pas tourner de manière circonférentielle par rapport auxdits rouages (185), ne peuvent pas se déplacer axialement à l'écart dudit premier rotor (65), et caractérisé en ce que le couple est entraîné entre le premier rotor (65) et le second rotor (70), et en ce que le second rotor (70) est configuré pour maintenir des aubes.


     




    Drawing


























    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