WO2016068858A1

WO2016068858A1 - Flange cooling system for hot gas path plenums in a turbine engine

Info

Publication number: WO2016068858A1
Application number: PCT/US2014/062501
Authority: WO
Inventors: Muzaffer Sutcu
Original assignee: Siemens Aktiengesellschaft
Priority date: 2014-10-28
Filing date: 2014-10-28
Publication date: 2016-05-06

Abstract

A hot gas path plenum (10) for a gas turbine engine (12) with a cooling system (14) positioned within one or more flanges of the plenum (10), whereby the cooling system (14) includes one or more channels (18) on a mating surface (20, 24) enabling formation intricate cooling configurations is disclosed. The cooling system (14) may include one or more cooling channels (18) that may be milled into one or more mating surfaces (20, 24) of mating flanges (16, 22) such that when the mating surfaces (20, 24) of the flanges (16, 22) are mated together, the cooling channels (18) are closed within the flanges (16, 22), thereby enabling high pressure gases to pass through the cooling channels (18) to cool the flanges (16, 22) and adjacent turbine components. By forming the cooling channels (18) within the mating surfaces (20, 24) of the mating flanges (16, 22), the cooling channels (18) are not limited to being only linear channels, but may include nonlinear channels and other more intricate configurations to efficiently and effectively cool the mating flanges (16, 22).

Description

FLANGE COOLING SYSTEM FOR HOT GAS PATH PLENUMS

IN A TURBINE ENGINE

FIELD OF THE INVENTION

This invention is directed generally to gas turbine engines and, more particularly, to cooling systems for joints in hot gas path plenums.

BACKGROUND

Typically, gas turbine engines include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power. Combustors often operate at high temperatures that may exceed 2,250 degrees Fahrenheit. Typical turbine combustor configurations expose turbine components to these high temperatures. Hot gas enclosures within the turbine engine typically have high pressure, compressor air on the outside of the enclosures and low pressure, hot combustion gases within the enclosures. Some of the higher pressure external cold compressed air is directed through the walls of the ducts for cooling the metallic wall.

Flanges joining hot gas path enclosure structures are subject to uneven internal hot gas flow as well as external cooling fluid flow on the cold external side of the enclosure structure. The flanges with uneven temperature distribution are susceptible to warping, which may cause gaps to develop at adjoining surfaces. Flanges typically have thicker walls than typical walls of hot gas components and vessels. Flanges are more difficult to cool due to the thickness of the structure. In addition, bolting or other fastening hardware and sealing gaskets are exposed to high temperatures, further complicating the flange connection.

Conventional cooling holes drilled through enclosure walls of structures are used to ensure that metallic walls exposed to a hot gas path are not subject to excessive thermal loads. Cooling holes positioned within flanges on hot gas path components are formed via drilling and are limited to being formed as linear cooling holes. Because of the increase thickness of the flanges, the cooling holes are often expensive to form due to the small diameter and long length. Thus, a need exists for a more efficient, less costly cooling system. SUMMARY OF THE INVENTION

A hot gas path plenum for a gas turbine engine with a cooling system positioned within one or more flanges of the plenum, whereby the cooling system includes one or more channels on a mating surface enabling formation intricate cooling configurations is disclosed. The cooling system may include one or more cooling channels that may be milled into one or more mating surfaces of mating flanges such that when the mating surfaces of the flanges are mated together, the cooling channels are closed within the flanges, thereby enabling high pressure gases to pass through the cooling channels to cool the flanges and adjacent turbine components. By forming the cooling channels within the mating surfaces of the mating flanges, the cooling channels are not limited to being only linear channels, but may include nonlinear channels and other more intricate configurations to efficiently and effectively cool the mating flanges.

In at least one embodiment, the hot gas path plenum for a gas turbine engine may include a first hot gas path channel having a first hot gas path flange and a second hot gas path channel having a second hot gas path flange. The second hot gas path flange may have one or more mating surfaces configured to mate with one or more mating surfaces of the first hot gas path flange. The hot gas path plenum may also include a flange cooling system having one or more cooling channels in the mating surface of the first hot gas path flange. The cooling channel may include an inlet at a high pressure surface of the first hot gas path flange and an outlet at a low pressure surface of the first hot gas path flange. The cooling channel may have an opening in the mating surface that is not closed until the mating surface of the first hot gas path flange mates with the mating surface of the second hot gas path flange.

In at least one embodiment, the cooling channel of the flange cooling system may be at least partially nonlinear relative to a longitudinal axis, such as over only a portion of a length of the cooling channel. In another embodiment, the cooling channel of the flange cooling system may be nonlinear. The cooling channel of the first hot gas path flange may include a plurality of cooling channels in the mating surface. Each of the cooling channels in the mating surface of the first hot gas path flange may include an inlet at a high pressure surface of the first hot gas path flange and an outlet at a low pressure surface of the first hot gas path flange. Each of the cooling channels may be nonlinear.

In at least one embodiment, the mating surface of the first hot gas path flange may include a first section of a cooling channel, and the mating surface of the second hot gas path flange may include a second section of the cooling channel, whereby at least a portion of the first and second sections are aligned when the mating surface of the first hot gas path flange is mated to the mating surface of the second hot gas path flange. An entire length of the first and second sections may be aligned when the mating surface of the first hot gas path flange is mated to the mating surface of the second hot gas path flange. The first and second sections of the cooling channel of the flange cooling system may be nonlinear. The cooling channel may be formed from a plurality of cooling channels forming first sections in the mating surface of the first hot gas path flange and a plurality of cooling channels forming second sections in the mating surface of the second hot gas path flange. A plurality of the first sections in the mating surface of the first hot gas path flange may be aligned with a plurality of second sections in the mating surface of the second hot gas path flange. All of the first sections in the mating surface of the first hot gas path flange may be aligned with the plurality of second sections in the mating surface of the second hot gas path flange.

An advantage of the flange cooling system is that the flange cooling system enables cooling channels to be nonlinear, such as, but not limited to being curved, one or more compound curves within a single cooling channel, and other nonlinear configurations to enhance to cooling efficiency of the flange cooling system within the flanges of a hot gas path component.

Another advantage of the flange cooling system is that the flange cooling system provides better cooling air distribution resulting in more uniform metal temperatures and better optimization of cooling air.

These and other embodiments are described in more detail below. BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying drawings, which are incorporated in and form a part of the specification, illustrate embodiments of the presently disclosed invention and, together with the description, disclose the principles of the invention.

Figure 1 is a cross-sectional view of a conventional flanged joint between two channels that contain combustion exhaust gases within an environment outside of the channels that is filled with compressor air.

Figure 2 is a partial cross-sectional, perspective view of a gas turbine engine including a hot gas path plenum with a cooling system.

Figure 3 is a cross-sectional view of a flanged joint between two channels that contain combustion exhaust gases within an environment outside of the channels that is filled with compressor air, wherein a cooling system is positioned within the flanged joint.

Figures 4a and 4b are perspective views of an embodiment of the cooling system with two flanges that, when combined, form a flanged joint, whereby at least one of the flanges includes cooling channels within a mating surface of the flange.

Figure 5a and 5b are perspective views of another embodiment of the cooling system with two flanges that, when combined, form a flanged joint, whereby at least one of the flanges includes cooling channels within a mating surface of the flange.

Figure 6 is a perspective view of another embodiment of the cooling system with flanges including cooling channels within a mating surface of the flange and including a conical aspect of the flange.

Figure 7 is a detail view of the flange of Figure 6.

Figure 8a is a cross-sectional view taken at section line 8-8 in Figure 7.

Figure 8b is a partial a cross-sectional view of a second hot gas path flange with a female conical section configured to mate with the male conical section shown in Figure 8a.

Figure 9 is a perspective view of yet another embodiment of the cooling system with flanges including cooling channels extending through a mating surface of the flange and including a conical aspect of the flange.

Figure 10 is a detail view of the flange of Figure 9.

Figure 1 1 is a cross-sectional view taken at section line 1 1 -1 1 in Figure 10. Figure 12 is an end view of another embodiment of the cooling system with flanges including cooling channels that exhaust cooling fluids into the hot gas path downstream from the joint formed at the flange between two adjacent transition sections.

Figure 13 is a perspective view of another embodiment of the cooling system with flanges including cooling channels that exhaust cooling fluids into the hot gas path downstream from the joint formed at the flange between two adjacent transition sections. DETAILED DESCRIPTION OF THE INVENTION

As shown in Figures 1 -13, a hot gas path plenum 10 for a gas turbine engine 12 with a cooling system 14 positioned within one or more flanges 16 of the plenum 10, whereby the cooling system 14 includes one or more channels 18 on a mating surface 20, 24 enabling formation intricate cooling configurations is disclosed. The cooling system 14 may include one or more cooling channels 18 that may be milled into one or more mating surfaces 20, 24 of mating flanges 16, 22 such that when the mating surfaces 20, 24 of the flanges 16, 22 are mated together, the cooling channels 18 are closed within the flanges 16, 22, thereby enabling high pressure gases to pass through the cooling channels 18 to cool the flanges 16, 22 and adjacent turbine components. By forming the cooling channels 18 within the mating surfaces 20, 24 of the mating flanges 16, 22, the cooling channels 18 are not limited to being only linear channels, but may include nonlinear channels 18 and other more intricate configurations to efficiently and effectively cool the mating flanges 16, 22.

In at least one embodiment, as shown in Figures 1 and 3-5, the hot gas path plenum 10 for a gas turbine engine 12 may include a first hot gas path channel 26 having a first hot gas path flange 16. The hot gas path plenum 10 may also include a second hot gas path channel 28 having a second hot gas path flange 22, wherein the second hot gas path flange 22 may have one or more mating surfaces 20 configured to mate with one or more mating surfaces 20 of the first hot gas path flange 16. The hot gas path plenum 10 may have any appropriate configuration, shape and size. The hot gas path plenum 10 may be tubular or have another appropriate shape. The first and second hot gas path channels 26, 28 may have the same configuration or different configurations, sizes or shapes. The first and second hot gas path channels 26, 28 may be transitions or other appropriate turbine components. The first and second hot gas path channels 26, 28 may be configured to contain hot combustion gases within the first and second hot gas path channels 26, 28 within an environment 30 surrounding the first and second hot gas path channels 26, 28 of high pressure compressor air.

The flange cooling system 14 may include one or more cooling channels 18 in the mating surface 20 of the first hot gas path flange 16. The cooling channel 18 may include an inlet 32 at a high pressure surface 34 of the first hot gas path flange 16 and an outlet 36 at a low pressure surface 38 of the first hot gas path flange 16. The cooling channel 18 may have an opening 40 in the mating surface 20 that is not closed until the mating surface 20 of the first hot gas path flange 16 mates with the mating surface 24 of the second hot gas path flange 22. The cooling channel 18 may be milled into the mating surface 20. As such, the configuration of the cooling channel 18 is not limited to being only linear as conventionally drilled cooling channels. Rather, the cooling channel 18 may be partially nonlinear relative to a longitudinal axis of the cooling channel 18 such that only a portion of the length of the cooling channel 18 is nonlinear. In another embodiment, the cooling channel 18 may be nonlinear along the entire length of the cooling channel 18.

In at least one embodiment, the flange cooling system 14 may include a plurality of cooling channels 18 in the mating surface 20. One or more of the cooling channels 18 may include an inlet 32 at the high pressure surface 34 of the first hot gas path flange 16 and an outlet 36 at a low pressure surface 38 of the first hot gas path flange 22. Some of the channels 18 may include inlets 32 attached to other cooling channels 18. In at least one embodiment, each of the cooling channels 18 in the mating surface 20 of the first hot gas path flange 16 may include an inlet 32 at the high pressure surface 34 of the first hot gas path flange 16 and an outlet 36 at the low pressure surface 38 of the first hot gas path flange 16. Each of the cooling channels 18 may be nonlinear.

In at least one embodiment, as shown in Figures 5a and 5b, the flange cooling system 14 may include one or more cooling channels 18 in the mating surface 20 of the first hot gas path flange 16 that forms a first section 42 of the cooling channel 18. The mating surface 24 of the second hot gas path flange 22 may include a second section 44 of the cooling channel 18. At least a portion of the first and second sections 42, 44 may be aligned when the mating surface 20 of the first hot gas path flange 16 is mated to the mating surface 24 of the second hot gas path flange 22. In at least one embodiment, an entire length of the first and second sections 42, 44 may be aligned when the mating surface 20 of the first hot gas path flange 16 is mated to the mating surface 24 of the second hot gas path flange 22. The first or second sections 42, 44, or both, may be partially nonlinear relative to a longitudinal axis of the cooling channel 18 such that only a portion of the length of the first and second sections 42, 44 may be nonlinear. In another embodiment, the first or second sections 42, 44, or both, may be nonlinear along the entire length of the first and second sections 42, 44. In at least one embodiment, the mating surface 20 of the first hot gas path flange 16 may include a plurality of first sections 42 of cooling channels 18, and the mating surface 24 of the second hot gas path flange 22 may include a plurality of second sections 44 of cooling channels 18. One or more of the first sections 42 in the mating surface 20 of the first hot gas path flange 16 may be aligned with one or more of the second sections 44 in the mating surface 24 of the second hot gas path flange 22. In at least one embodiment, a plurality of first sections 42 in the mating surface 20 of the first hot gas path flange 16 may be aligned with a plurality of the second sections 44 in the mating surface 24 of the second hot gas path flange 22. In yet another embodiment, all of the first sections 42 in the mating surface 20 of the first hot gas path flange 16 may be aligned with the all of second sections 44 in the mating surface 24 of the second hot gas path flange 22.

In another embodiment, as shown in Figures 6-8b, the flange cooling system

14 may include one or more cooling channels 18 in the mating surface 20 of the first hot gas path flange 16 on the hot gas path plenum 10. The flange 16 may include a male conical section 50 extending radially inward and toward a mating face of an adjacent flange 16 on a hot gas path plenum 10. One or more channels 18 may extend along the mating surface 20 of the flange 16 and the male conical section 50. A second hot gas path channel 28 may include a matching female conical section 52 on the second hot gas path flange 22 to receive the male conical section 50. Cooling channels 18 may be included on the first and second hot gas path flanges 16 and 22, as previously set forth. The cooling channels 18 in the first and second hot gas path flanges 16 and 22 may be aligned with each other to form channels formed by both the cooling channels 18 with the first and second hot gas path flanges 16 and 22. The cooling channels 18 may extend radially outward or at other orientations, as shown in Figure 6.

In another embodiment, as shown in Figures 9-1 1 , the cooling channels 18 may extend along a radially outer surface 54 of the male conical section 50 and into the first hot gas path flange 16. The cooling channels 18 may include exhaust outlets 56 on non-mating surfaces 58 of the first hot gas path flange 16. The cooling channels 18 extending into the first hot gas path flange 16 cools first hot gas path flange 16.

In another embodiment, as shown in Figures 12 and 13, the flange cooling system 14 may include one or more cooling channels 18 in the mating surface 20 of the first hot gas path flange 16 on the hot gas path plenum 10. The cooling channels 18 may include exhaust outlets 60 in fluid communication with one or more mainfold channels 62. In at least one embodiment, the manifold channel 62 may be positioned radially inward of the exhaust outlets 60. One or more exhaust channels 64 may extend from an inlet 66 at the manifold channel 62 to an outlet 68 on an inner surface 70 of the first hot gas path channel 26 of the hot gas path plenum 10.

During turbine engine operation, compressor air in the environment 30 outside of the hot gas path plenum 10 is at a higher pressure and lower temperature than the combustion exhaust gases within the hot gas path plenum 10. The compressor air in the environment 30 passes into the one or more inlets 32 and into the cooling channels 18 at the mating surfaces 20, 24 of the first and second hot gas path flanges 16, 22. The compressor air cools the mating surfaces 20, 24 of the first and second hot gas path flanges 16, 22 and flows toward the inner flow path of the hot gas path plenum 10 where the compressor air is exhausted through the one or more outlets 36.

The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.

Claims

CLAIMS We claim:

1 . A hot gas path plenum (10) for a gas turbine engine (12), characterized in that:

a first hot gas path channel (26) having a first hot gas path flange (16);

a second hot gas path channel (28) having a second hot gas path flange (22), wherein the second hot gas path flange (22) has at least one mating surface (24) configured to mate with at least one mating surface (20) of the first hot gas path flange (16); and

a flange cooling system (14) having at least one cooling channel (18) in the at least one mating surface (20) of the first hot gas path flange (16), wherein the at least one cooling channel (18) includes an inlet (32) at a high pressure surface (34) of the first hot gas path flange (16) and an outlet (36) at a low pressure surface (38) of the first hot gas path flange (16) and wherein the at least one cooling channel (18) has an opening (40) in the at least one mating surface (20) that is not closed until the at least one mating surface (20) of the first hot gas path flange (16) mates with the at least one mating surface (24) of the second hot gas path flange (22).

2. The hot gas path plenum (10) for a gas turbine engine (12) of claim 1 , characterized in that the at least one cooling channel (18) of the flange cooling system (14) is at least partially nonlinear.

3. The hot gas path plenum (10) for a gas turbine engine (12) of claim 1 , characterized in that the at least one cooling channel (18) of the flange cooling system (14) is nonlinear.

4. The hot gas path plenum (10) for a gas turbine engine (12) of claim 1 , characterized in that the at least one cooling channel (18) in the at least one mating surface (20) of the first hot gas path flange (16) comprises a plurality of cooling channels (18) in the at least one mating surface (20).

5. The hot gas path plenum (10) for a gas turbine engine (12) of claim 4, characterized in that each of the cooling channels (18) in the at least one mating surface (20) of the first hot gas path flange (16) includes an inlet (32) at a high pressure surface (34) of the first hot gas path flange (16) and an outlet (36) at a low pressure surface (38) of the first hot gas path flange (16).

6. The hot gas path plenum (10) for a gas turbine engine (12) of claim 4, characterized in that each of the cooling channels (18) is nonlinear.

7. The hot gas path plenum (10) for a gas turbine engine (12) of claim 1 , characterized in that the at least one cooling channel (18) in the at least one mating surface (20) of the first hot gas path flange (16) forms a first section (42) of the at least one cooling channel (18) and wherein the at least one mating surface (24) of the second hot gas path flange (22) further comprises a second section (44) of the at least one cooling channel (18), whereby at least a portion of the first and second sections (42, 44) are aligned when the at least one mating surface (20) of the first hot gas path flange (16) is mated to the at least one mating surface (24) of the second hot gas path flange (22).

8. The hot gas path plenum (10) for a gas turbine engine (12) of claim 7, characterized in that an entire length of the first and second sections (42, 44) are aligned when the at least one mating surface (20) of the first hot gas path flange (16) is mated to the at least one mating surface (24) of the second hot gas path flange (22).

9. The hot gas path plenum (10) for a gas turbine engine (12) of claim 7, characterized in that the first and second sections (42, 44) of the at least one cooling channel (18) of the flange cooling system (14) is nonlinear.

10. The hot gas path plenum (10) for a gas turbine engine (12) of claim 7, characterized in that the at least one cooling channel (18) comprises a plurality of cooling channels (18) forming first sections (42) in the at least one mating surface (20) of the first hot gas path flange (16) and a plurality of cooling channels (18) forming second sections (44) in the at least one mating surface (24) of the second hot gas path flange (22).

1 1 . The hot gas path plenum (10) for a gas turbine engine (12) of claim 10, characterized in that a plurality of the first sections (42) in the at least one mating surface (20) of the first hot gas path flange (16) are aligned with a plurality of second sections (44) in the at least one mating surface (24) of the second hot gas path flange (22).

12. The hot gas path plenum (10) for a gas turbine engine (12) of claim 10, characterized in that all of the first sections (42) in the at least one mating surface (20) of the first hot gas path flange (16) is aligned with the plurality of second sections (44) in the at least one mating surface (24) of the second hot gas path flange (22).

13. The hot gas path plenum (10) for a gas turbine engine (12) of claim 1 , characterized in that the first hot gas path flange (16) includes at least one male conical section (50) that mates with at least one female conical section (52) of the second hot gas path flange (22).

14. The hot gas path plenum (10) for a gas turbine engine (12) of claim 1 , characterized in that the at least one cooling channel (18) extends through the first hot gas path flange (16).

15. The hot gas path plenum (10) for a gas turbine engine (12) of claim 1 , characterized in that the at least one cooling channel (18) includes an exhaust outlet (56) that is in fluid communication with at least one mainfold channel (62) and at least one exhaust channel (64) extending from an inlet (32) at the at least one manifold channel (62) to an outlet (36) on an inner surface (70) of the first hot gas path channel (26).