WO2018080474A1

WO2018080474A1 - Liner for a transition duct

Info

Publication number: WO2018080474A1
Application number: PCT/US2016/058823
Authority: WO
Inventors: Robet H. BARTLEY
Original assignee: Siemens Aktiengesellschaft
Priority date: 2016-10-26
Filing date: 2016-10-26
Publication date: 2018-05-03

Abstract

A liner (10) for a gas turbine engine is inserted into a channel (12) located in a inlet ring (11) of a transition duct (8). The liner is formed as a flat unitary piece with angled ends (14). The angled ends complement each other. When installed the liner is biased against the walls of the channel.

Description

LINER FOR A TRANSITION DUCT

BACKGROUND

[0001] 1. Field

[0002] Disclosed embodiments are generally related to gas turbine engines and, more particularly, to the transition system used in gas turbine engines.

[0003] 2. Description of the Related Art

[0004] A gas turbine engine typically has a compressor section, a combustion section having a number of combustors and a turbine section. Ambient air is compressed in the compressor section and conveyed to the combustors in the combustion sectioa The combustors combine the compressed air with a fuel and ignite the mixture creating combustion products. The combustion products flow in a turbulent manner and at a high velocity. The combustion products are routed to the turbine section via transition ducts. Within the turbine section are rows of vane assemblies. Rotating blade assemblies are coupled to a turbine rotor. As the combustion product expands through the turbine section, the combustion product causes the blade assemblies and turbine rotor to rotate. The turbine rotor may be linked to an electric generator and used to generate electricity.

[0005] During the operation of gas turbine engines strong forces are generated that can impact the structure of the gas turbine engine. These forces may occur in the transition duct. Accommodating these forces to avoid breakage is important for the continued operation of the gas turbine engine.

SUMMARY

[0006] Briefly described, aspects of the present disclosure relate to the inlet of the transition duct

[0007] An aspect of the disclosure may be an inlet ring for a gas turbine engine comprising: a channel formed in a wall, wherein the channel extends around a circumference of the inlet ring; and a liner insertable into the channel, wherein the liner engages a portion of a combustor basket inserted into the inlet ring, wherein the liner is replaceable. [0008] Another aspect of the disclosure may be a gas turbine engine comprising: a combustor basket; a transition duct located downstream of the combustor basket, wherein the transition duct comprises; an inlet ring, wherein the combustor basket is insertable into the inlet ring; a channel formed in a wall of the inlet ring, wherein the channel extends around a circumference of the inlet ring; and a liner insertable into the channel of the inlet ring, wherein the liner engages a portion of the combustor basket, wherein the liner is replaceable.

[0009] Still another aspect of the disclosure may be a method for replacing a liner in a gas turbine engine comprising; removing the liner inserted into a channel of an inlet ring of the gas turbine engine, wherein the liner has formed a ring biased against a wall of the channel; and inserting a replacement liner into the channel of the inlet ring, wherein the replacement liner forms a ring biased against the wall of the channel.

BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Fig. 1 is a view of the liner.

[0011] Fig.2 shows a view of me transition duct and liner.

[0012] Fig. 3 is a view of the transition duct with the liner inserted.

[0013] Fig. 4 is a cut away view of the transition duct and liner.

[0014] Fig. 5 is a view of the spring chp of the combustor basket of the combustor basket interacting with the liner.

DETAILED DESCRIPTION

[0015] 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.

[0016] 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.

[0017] During operation of a gas turbine engine there are tremendous forces generated. These forces can cause structural fatigue to the components that form the gas turbine engine. One area where structural fatigue can occur is within the transition duct that is connected to the combustor basket. Wear and tear at the point of connection can necessitate the replacement of the transition duct.

[0018] The inventor recognized that instead of having to replace the entire transition duct or inlet ring the portion of the transition duct that interacts with the combustor basket can be made of a different material. This different material would preferably be a material that is less inclined to suffer structural fatigue during the operation of the gas turbine engine. Also, preferably, that portion of the transition duct can be replaceable so that complete replacement of the transition duct does not need to occur.

[0019] Figs. 1-5 show views of a liner 10 that can be inserted into an inlet ring 11 of a transition duct 8. The liner 10 is inserted into the inlet ring 11 at the location where the sealing means, such as spring clip 18 of the combustor basket 16 engages the inlet ring 11, shown in Fig. 5. By having the liner 10 engage the sealing means of the combustor basket 16 the liner 10 can suffer the wear and tear that occurs during operation of the gas turbine engine. The liner 10 may then be replaced when needed instead of the inlet ring 11. Additionally the material of the liner 10 may be optimized for its particular purpose and may therefore be made of a different material than the inlet ring 11. The liner 10 may be optimized to reduce wear and tear on itself or it may be optimized to reduce wear on the sealing means of the combustor basket 16. The liner 10 may also be made of a less expensive material or permit the inlet ring 11 to be made of a less expensive material.

[0020] Fig. 1 shows the liner 10 before being prepared for insertion into the inlet ring 11 of the transition duct 8. In Fig. 1 the liner 10 is flat and not yet formed into a ring. The liner 10 may be made of material different from the material that forms the transition duct 8. Preferably the material used for the liner 10 is made of a more durable material than the material that forms the transition duct 8. The liner 10 may also have a wear coating. Possible materials that may be used for the liner 10 are Haynes 188, Haynes 25, Nimonic 90, Titam^'um-Zirconium-Molybdenum alloy TZM. HS-21, Haynes, Hperco, Stellite, Astroby, Hastelloy, Iconel, IN 100, Merl, Waspaloy, Monel, Rene and Incoloy, as well as other materials.

[0021] The ends 14 of the liner 10 are slanted. The slant formed is such that one end 14 complements the other end 14 when forming a ring. In the embodiment shown in Fig. 1, each end 14 forms a slant with a 45 degree angle. Each end 14 may have a slant that has an angle other than 45 degrees. However, preferably the two slanted ends 14 complement each other. For example if one end 14 had a slant with an angle of 30 degrees then the other end 14 should have an angle of 60 degrees. The ends 14 of the liner 10 are slanted to limit leakage when installed into the transition duct 8 and to limit the wear of the Kner 10.

[0022] Fig. 2 shows the liner 10 formed into a ring and prior to insertion into the inlet ring llof the transition duct 8. Fig. 3 shows the liner 10 inserted into and installed into the inlet ring 11 of the transition duct 8. The liner 10 is dimensioned so as to permit the formation of a ring. Preferably the liner 10 is dimensioned so as to form a ring that is biased to return to its original state.

[0023] Fig. 4 shows a cut away view of the liner 10 inserted into the inlet ring 11 of the transition duct 8. The transition duct 8 and inlet ring 11 are designed to be used with a gas turbine engine and may be made of metal or ceramic. The transition duct 8 carries hot working gases from the combustor downstream to the turbine blades. Formed within the inlet ring 11 of the transition duct 8 is a channel 12.

[0024] The channel 12 formed in the transition duct 8 is annular and runs around the circumference of the inlet ring 11 of the transition duct 8. The depth of the channel 12 may be about the same thickness of the liner 10 that is inserted therein. However, it should be understood that the depth of the channel 12 may be more or less than the thickness of the liner 10 and is preferably slightly more than the thickness of the liner 10.

[0025] When inserted into the channel 12 the liner 10 is formed into a ring. The liner 10 is inserted and rolled into the channel 12. Preferably the circumference of the ring formed by the liner 10 is slightly larger than the circumference of the channel 12.

[0026] The ends 14 of the liner 10 may overlap. The liner 10 then expands into the channel 12 due to the material properties of the liner 10. That is to say the liner 10 wants to return to its flattened state. This tendency to return to the flattened state biases the liner 10 against the walls of the channel 12. Once installed there may be a small gap between the two ends 14 of the liner 10 and the ends 14 may not contact each other once installed.

[0027] Fig. 5 shows a cut away view of the combustor basket 16 inserted into the inlet ring 11 of the transition duct 8. The sealing means of the combustor basket 16 engage the liner 10. In the embodiment shown in Fig. 5 the sealing means may be spring clips 18. The spring clips 18 further bias the liner 10 against the walls of the channel 12.During operation of the gas turbine engine, it is the liner 10 that undergoes wear and tear rather man the inlet ring 11. Once the liner 10 suffers too much material fatigue it may easily be replaced. This can increase the overall lifespan of the transition duct 8.

[0028] While embodiments of the present disclosure have been disclosed in exemplary forms, it will be apparent to those skilled in the art mat 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. An inlet ring for a gas turbine engine comprising:

a channel formed in a wall, wherein the channel extends around a

circumference of the inlet ring; and

a liner insert able into the channel, wherein the liner engages a portion of a combustor basket inserted into the inlet ring, wherein the liner is replaceable.

2. The inlet ring of claim 1, wherein the liner forms a ring.

3. The inlet ring of claim 2, wherein a circumference of a ring formed by the liner is larger than a circumference of the channel.

4. The inlet ring of claim 1, wherein the liner is biased against the wall of the channel.

5. The inlet ring of claim 1, wherein the liner has two ends, wherein each of the two ends is slanted.

6. The inlet ring of claim 5, wherein the two ends complement each other when the liner forms a ring.

7. The inlet ring of claim 5, wherein the ends of the liner do not contact each other after installatioa

8. The inlet ring of claim 5, wherein the ends of the liner overlap each other during installation.

9. The inlet ring of claim 1 , wherein a spring clip of the combustor basket engages the liner when the combustor basket is inserted.

10. The inlet ring of claim 1, wherein the liner is made of a different material than the inlet ring.

11. A gas turbine engine comprising:

a combustor basket;

a transition duct located downstream of the combustor basket, wherein the transition duct comprises;

an inlet ring, wherein the combustor basket is insertable into the inlet ring;

a channel formed in a wall of the inlet ring, wherein the channel extends around a circumference of the inlet ring; and

a liner insertable into the channel of the inlet ring, wherein the liner engages a portion of the combustor basket, wherein the liner is replaceable.

12. The gas turbine engine of claim 11, wherein the circumference of a ring formed by the liner is larger than a rircumference of the channel.

13. The gas turbine engine of claim 11, wherein the liner is biased against the wall of the channel.

14. The gas turbine engine of claim 11, wherein the liner has two ends, wherein each of the two ends is slanted.

15. The gas turbine engine of claim 14, wherein the two ends complement each other when the Hner forms a ring.

16. The gas turbine engine of claim 14, wherein the ends of the liner do not contact each other after installation.

17. The gas turbine engine of claim 14, wherein the ends of the liner overlap each other during installatioa

18. The gas turbine engine of claim 11, wherein a spring clip of the combustor basket engages the liner when the combustor basket is inserted.

19. A method for replacing a liner in a gas turbine engine comprising;

removing the liner inserted into a channel of an inlet ring of the gas turbine engine, wherein the liner has formed a ring biased against a wall of the channel; and

inserting a replacement liner into the channel of the inlet ring, wherein the replacement liner forms a ring biased against the wall of the channel.

20. The method of claim 19, wherein the replacement liner is inserted into the channel so that two ends of the replacement liner complement each other when forming the ring.