WO2018128600A1

WO2018128600A1 - Side seal for the transition duct system of a gas turbine engine

Info

Publication number: WO2018128600A1
Application number: PCT/US2017/012103
Authority: WO
Inventors: Robert H. Bartley; Daniel CASSAR
Original assignee: Siemens Aktiengesellschaft
Priority date: 2017-01-04
Filing date: 2017-01-04
Publication date: 2018-07-12

Abstract

A gas turbine engine (10) has a side seal (25a) located between adjacent exit pieces. The side seal (25a) comprises a first seal side (23a) and a second seal side (24a) that contact each other. The first seal side (23a) has a spring (26a) that biases the first seal side (23a) in the direction of the second seal side (24a). The first seal side moves independently from the second seal side. The side seal (25a) is able to provide a seal while accommodating the motion and deformation generated by the gas turbine engine (10). This minimizes wear and tear of the side seal (25a).

Description

SIDE SEAL FOR THE TRANSITION DUCT SYSTEM OF A GAS TURBINE ENGINE

BACKGROUND

[0001] 1. Field

[0002] Disclosed embodiments are generally related to gas turbine engines and more particularly to the transition system of a gas turbine engine.

[0003] 2. Description of the Related Art

[0004] Gas turbine engines typically have transition ducts to conduct and direct the gasses from combustors to rows of turbine blades. The transition ducts as well as vanes orient the combustion gas flow streams to contact the turbine blades at preferred angles for rotation of the blades.

[0005] In some gas turbine engines, the transition ducts are arranged in an array. The spaces between adjacent transition ducts may permit compressor discharge air to bypass the combustion system. Therefore effective sealing of the spaces between adjacent transition ducts is desired.

SUMMARY

[0006] Briefly described, aspects of the present disclosure relate to side seals used in gas turbine engines.

[0007] An aspect of present disclosure may be a gas turbine engine comprising a first exit piece connected to a first transition duct, wherein the first exit piece has a first channel formed therein. The gas turbine engine also has a second exit piece connected to a second transition duct, wherein the second exit piece has a second channel formed therein, wherein the second exit piece is adjacent to the first exit piece. The gas turbine engine also has a side seal located in the first channel and the second channel, the side seal comprising; a first seal side and a second seal side; wherein the first seal side comprises a spring that biases the first seal side towards the second seal side, wherein the second seal side has a surface that contacts the first seal side; and wherein the first seal side moves independently from the second seal side to accommodate movement of the first exit piece and the second exit piece during operation of the gas turbine engine. [0008] Another aspect of the present disclosure may be a side seal for a gas turbine engine comprising a first seal side adapted to be placed in a first channel of a first exit piece. The side seal also has a second seal side adapted to be placed in a second channel of a second exit piece, wherein the first seal side comprises a spring that biases the first seal side towards the second seal side, wherein the second seal side has a surface that contacts the first seal side; and wherein the first seal side moves independently from the second seal side to accommodate movement of the first exit piece and the second exit piece during operation of the gas turbine engine.

BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Fig. 1 shows a side cross-sectional view of a gas turbine engine.

[0010] Fig. 2 shows a view of the transition ducts, exit pieces and side seal located there between.

[0011] Fig. 3 shows a view of a side seal.

[0012] Fig. 4 shows a top down view of the transition ducts, exit pieces and side seal located there between.

[0013] Fig. 5 shows a top down view of the transition ducts, exit pieces and side seal after movement of the transition duct and integrated piece.

[0014] Fig. 6 shows a view of an IEP exhibiting deformation of a side rail.

[0015] Fig. 7 shows a top down view of the transition ducts, exit pieces and an alternative embodiment of a side seal.

[0016] Fig. 8 shows a top down view of the transition ducts, exit pieces and another alternative embodiment of a side seal.

[0017] Fig. 9 shows a view of an alternative engagement of the seal sides. [0018] Fig. 10 shows a view of an alternative embodiment of a side seal. [0019] Fig. 11 shows an alternative embodiment of a side seal. [0020] Fig. 12 shows another alternative embodiment of a side seal. DETAILED DESCRIPTION

[0021] To facilitate an understanding of embodiments, principles, and features of the present disclosure, they are explained hereinafter with reference to implementation in illustrative embodiments. Embodiments of the present disclosure, however, are not limited to use in the described systems or methods.

[0022] The components and materials described hereinafter as making up the various embodiments are intended to be illustrative and not restrictive. Many suitable components and materials that would perform the same or a similar function as the materials described herein are intended to be embraced within the scope of embodiments of the present disclosure.

[0023] Fig. 1 shows a cross-sectional view of a gas turbine engine 100 showing a transition system 10 having transition ducts 20. The inventor recognized that the side seals typically used between exit pieces tend to wear during operation. The deformation and motion of the transition ducts 20 during operation causes wear and tear on the side seals. This can reduce the life span of components and can cause high costs of repair. Therefore the inventor has developed side seals that are able to accommodate the wear and tear that is typically caused by the operation of the gas turbine engine.

[0024] Fig. 2 shows a transition duct 20a and a transition duct 20b located adjacent to each other. Located at a distal end of each of the transition ducts 20a, 20b are exit pieces and as used in the examples herein, integrated exit pieces (IEPs) 22a and 22b, respectively. Between IEP 22a and IEP 22b is a side seal 25a. Transition ducts 20a and 20b are typically part of a plurality of transition ducts that form an annular array. With respect to the annular array and as shown in Fig. 2 the circumferential direction C, the axial direction A and the radial direction R are indicated in order to provide orientation. Between IEP 22a and IEP 22b is a side seal 25a. Side seal 25a extends between IEP 22a and IEP 22b so that the longest dimension of the side seal 25a is in the radial direction R.

[0025] Turning to Figs. 3-6 shown are views of the side seal 25a made in accordance with an embodiment of the present disclosure and the placement of the side seal 25a with respect to the IEPs 22a and 22b. The side seal 25a is placed within IEP channel 21a and IEP channel 21b which are formed within the side rails 19a and 19b. The side seal 25a has a first seal side 23a and a second seal side 24a. It should be understood, that while the first seal side 23a and the second seal side 24 are shown with one being on one side and the other being on the other side these positions may be interchanged. Furthermore, it is also contemplated that first seal side 23a and second seal side 24a may also each be placed within cartridge housings (not shown) that can further engage portions of the IEP channels 21a and 21b and protect the first seal side 23a and second seal side 24a.

[0026] The first seal side 23a is formed from a rectangular portion 27a and a spring 26a. The rectangular portion 27a presents a flat surface to the second seal side 24a for purposes of engagement during operation of the gas turbine engine. The rectangular portion 27a is connected to the spring 26a. The spring 26a may be connected to the rectangular portion 27a via welding, brazing or other art recognized means for attachment.

[0027] The spring 26a is a sinusoidal shaped piece that when placed within the IEP channel 21a it is biased against the wall of the IEP channel 21a. However, it should be understood that any spring shape may be used that provides a biasing force. The biasing of the spring 26a pushes the rectangular portion 27a in the circumferential direction C towards the second seal side 24a. The engagement of the rectangular portion 27a with the second seal side 24a is able to accommodate movement back and forth in the axial direction A without excessive wear and tear.

[0028] The second seal side 24a is formed with a rectangular portion 28a which extends lengthwise in the circumferential direction C within the IEP channel 21b. Formed integrally with the rectangular portion 28a is the engagement portion 29a. It should be understood that rectangular portion 28a and engagement portion 29a may alternately be separately formed and joined. The engagement portion 29a extends in an axial direction A with respect to the rectangular portion 28a and the rectangular portion 27a. The junction between the rectangular portion 28a and the engagement portion 29a may form a right angle. If a cross-section is taken in the axial direction A the second seal side 24a has an "L" shaped cross-section. However other cross- sectional shapes may be used as well, such as a "T" shaped cross-section.

[0029] The engagement portion 29a presents a wide surface area for the rectangular portion 27a to engage. This provides a flat surface for engagement even when there is deformation of IEP channels 21a and 21b due to deformation of the side rails 19a and 19b, as shown in Fig. 6. The deformation of the side rails 19a and 19b may be due to heating. In addition to the engagement portion 29a providing a wide surface area, the engagement portion 29a also restricts movement of the second seal side 24a within the IEP channel 21b.

[0030] As illustrated in Figs. 4 and 5 looking top-down (radially inwards) at the IEP 20a and IEP 20b, the side seal 25a is able to accommodate movement caused by the operation of the gas turbine engine. In Figs. 4 and 5 the accommodated movement illustrated is movement in the axial direction A, however it should be understood that movement in the circumferential direction C and the radial direction R may also be accommodated by the side seal 25a.

[0031] Turning to Fig. 7 a side seal 25b is shown. Side seal 25b has first seal side 23b and a second seal side 24b. First seal side 23b has a rectangular portion 27b and a spring 26b similar to the first seal side 23a discussed above. Likewise the second seal side 24b has a rectangular portion 28b and an engagement portion 29b similar to the rectangular portion 28a and engagement portion 29b discussed above. However, rectangular portion 28a has a pin member 31b. The pin member 31b is designed to restrict movement within IEP channel 21b by engaging side rail 19b. The restriction of movement prevents disengagement of the side seal 25b and reduces potential for compromise of the seal. The pin member 31b may be separate from the rectangular portion 28a and is preferably adapted to permit the rectangular portion 28a to slide freely in the axial direction.

[0032] Turning to Fig. 8 a side seal 25c is shown. Side seal 25c has first seal side 23c and a second seal side 24c. First seal side 23c has a rectangular portion 27c and a spring 26c similar to the first seal side 23a discussed above. The second seal side 24c has a rectangular portion 28c and an engagement portion 29c similar to the rectangular portion 28a and engagement portion 29b discussed above. However, rectangular portion 28c additionally has a spring 26c. The spring 26c located on the rectangular portion 28c biases second seal side 24c in the direction of the first seal side 23c. This embodiment can provide additional flexibility and movement of the side seal 25c in order to accommodate the motion due to the operation of the gas turbine engine.

[0033] Turning to Fig. 9 a side seal 25d is shown that illustrates a different way of providing engagement between engagement portion 29d and rectangular portion 27d. The engagement portion 29d has a curved receiving section 33d that is adapted to receive rounded member 34d. The curved receiving section 33d has a hemispherical cross section. The rounded member 34d has a circular cross section. This embodiment provides a smooth engagement of the engagement portion 29d and rectangular portion 27d while also providing additional securement means to prevent any separation of contact between engagement portion 29d and rectangular portion 27d.

[0034] Fig. 10 shows the first seal side 23e of side seal 25e. In this embodiment the first seal side 23e may be subdivided into multiple components. This can provide additional flexibility when placed within IEP channel 21a. While Fig. 10 shows the first seal side 23 e subdivided into multiple components it should also be understood that other components of the side seal 25e may be subdivided as well.

[0035] Fig. 11 shows first seal side 23f of side seal 25f. In this embodiment, the rectangular portion 27f has a crossbar portion 32f connected to the spring 26f that extends in an axial direction so that it encompasses the width of the IEP channel 21a. The crossbar portion 32f is adapted to engage the side rail 19a and prevents dislodgement of the side seal 25f from the IEP channel 21a.

[0036] Fig. 12 shows side seal 25g. Side seal 25g takes advantage of the pressure differential on opposite sides of side seal 25g when placed within IEP channels 21a and 21b. In the axial upstream direction there is a pressure PI that is higher than the pressure P2 on the other side of side seal 25g in the downstream axial direction. This pressure differential is taken advantage of by the extension member 35. The extension member 35 extends in the upstream direction and is able to take advantage of the pressure. The pressure differential will bias the side seal 25g in the downstream axial direction in order to further prevent dislodgement during the operation of the gas turbine engine. The extension member 35 may be placed on either the first seal side 23g or the second seal side 24g. The surface of the extension member 35 that engages the second seal side 24g in Fig. 12 may be rounded so as to accommodate the movement imparted by the pressure differential. [0037] Additionally, upper and lower capping portions (not shown) may be attached to a first seal side or a second seal side in order to further prevent dislodgement of the side seal from within the IEP channels in a radial direction.

[0038] The embodiments disclosed herein provide a side seal that is able to minimize the wear and tear caused by movement of the IEPS during the operation of the gas turbine engine. In part this is due to having the side seal formed from a first seal side and a second seal that are able to engage each other with flat surfaces.

[0039] While embodiments of the present disclosure have been disclosed in exemplary forms, it will be apparent to those skilled in the art that many modifications, additions, and deletions can be made therein without departing from the spirit and scope of the invention and its equivalents, as set forth in the following claims.

Claims

What is claimed is:

1. A gas turbine engine comprising:

a first exit piece (22a) connected to a first transition duct (20a), wherein the first exit piece (22a) has a first channel (21a) formed therein;

a second exit piece (22b) connected to a second transition duct (20b), wherein the second exit piece (22b) has a second channel (21b) formed therein, wherein the second exit piece (22b) is adjacent to the first exit piece (22a);

a side seal (25a) located in the first channel (21a) and the second channel (21b), the side seal (25a) comprising;

a first seal side (23a) and a second seal side (24a);

wherein the first seal side (23a) comprises a spring (26a) that biases the first seal side (23a) towards the second seal side (24a),

wherein the second seal side (24a) has a surface that contacts the first seal side (23 a); and

wherein the first seal side (23a) moves independently from the second seal side (24a) to accommodate movement of the first exit piece (22a) and the second exit piece (22b) during operation of the gas turbine engine (10).

2. The gas turbine engine of claim 1, wherein the first seal (23a) side further comprises a rectangular portion (27a), wherein the rectangular portion (27a) contacts the surface of the second seal side (24a).

3. The gas turbine engine of any one of claims 1 or 2, wherein the second seal side (24b) further comprises a pin (3 lb).

4. The gas turbine engine of claim 3, wherein the pin (3 lb) retains the second seal side (24b) within the second channel (21b).

5. The gas turbine engine of any one of claims 1-4, wherein the second seal side (24c) further comprises a second spring (26c).

6. The gas turbine engine of any one of claims 1-5, wherein the second seal side (24d) further comprises a receiving section (33d) shaped to receive an engagement portion (29d) of the first seal side (23d).

7. The gas turbine engine of claim 6, wherein the receiving section (33d) has a hemispherical cross section, wherein the engagement portion (29d) has a circular cross section.

8. The gas turbine engine of any one of claims 1-7, wherein the first seal side (24e) is segmented.

9. The gas turbine engine of any one of claims 1-8, wherein the second seal side (23a) has an L shaped cross section.

10. The gas turbine engine of any one of claims 1-9, wherein the first seal side (23g) is biased against the surface of the first channel (21a) via a pressure differential caused during the operation of the gas turbine engine (10).

11. A side seal for a gas turbine engine comprising:

a first seal side (23a) adapted to be placed in a first channel (21a) of a first exit piece (22a);

a second seal side (24a) adapted to be placed in a second channel (21b) of a second exit piece (22b),

wherein the first seal side (23a) comprises a spring (26) that biases the first seal side (23a) towards the second seal side (24a),

wherein the second seal side (24a) has a surface that contacts the first seal side (23a); and

12. The side seal of claim 11, wherein the first seal side (23a) further comprises a rectangular portion (27a), wherein the rectangular portion (27a) contacts the surface of the second seal side (24a).

13. The side seal of any one of claims 11 or 12, wherein the second seal side (24a) further comprises a pin (3 lb).

14. The side seal of claim 13, wherein the pin (3 lb) is adapted to retain the second seal side (24b) within the second channel (21b).

15. The side seal of any one of claims 11-14, wherein the second seal side (24c) further comprises a second spring (26c).

16. The side seal of any one of claims 11-15, wherein the second seal side (24d) further comprises a receiving section (33d) shaped to receive an engagement portion (29d) of the first seal side (23d).

17. The side seal of claim 16, wherein the receiving section (33d) has a hemispherical cross section, wherein the engagement portion (29d) has a circular cross section.

18. The side seal of any one of claims 11-17, wherein the first seal side (24e) is segmented.

19. The side seal of any one of claims 11-18, wherein the second seal side (24a) has an L shaped cross section.

20. The side seal of any one of claims 11-18, wherein the first seal side (23g) is adapted to be biased against the surface of the first channel (21a).