WO2015069125A1

WO2015069125A1 - Turbomachine exhaust frame

Info

Publication number: WO2015069125A1
Application number: PCT/PL2013/000142
Authority: WO
Inventors: Srinivasa Rao PAKKALA; Przemyslaw Michal JAKUBCZAK; Piotr Edward KOBEK; Rohit Pruthi
Original assignee: General Electric Company
Priority date: 2013-11-08
Filing date: 2013-11-08
Publication date: 2015-05-14
Also published as: JP6266772B2; JP2016538456A; DE112013007581T5; CN105960511A; CN105960511B

Abstract

A turbomachine exhaust frame includes a body having an outer barrel member (50) including an outer surface and an inner surface and an inner barrel member (52) having an outer surface and an inner surface. A first flow passage (61) is defined by the outer surface and the inner surface of the outer barrel member. A second flow passage (68) is defined by the outer surface and the inner surface of the inner barrel member. A first cooling circuit (91) having a first inlet and a first outlet is connected to the first flow passage, and a second cooling circuit (94) having a second inlet and a second outlet is fluidically connected to the second flow passage. A nozzle (130) is arranged in the first flow passage and is connected to the first cooling circuit. The nozzle introduces a fluid flow into the first flow passage in at least one of an axial and an annular direction.

Description

TURBOMACHINE EXHAUST FRAME

BACKGROUND OF THE INVENTION

[0001] The subject matter disclosed herein relates to the art of turbomachines and, more particularly to a turbomachine exhaust frame. [0002] Turbomachines include a compressor portion linked to a turbine portion through a common compressor/turbine shaft and a combustor assembly. An inlet airflow is passed through an air intake toward the compressor portion. In the compressor portion, the inlet airflow is compressed through a number of sequential stages toward the combustor assembly. In the combustor assembly, the compressed airflow mixes with a fuel to form a combustible mixture. The combustible mixture is combusted in the combustor assembly to form hot gases. The hot gases are guided along a hot gas path of the turbine portion through a transition piece. The hot gases expand through a number of turbine stages acting upon turbine buckets mounted on wheels to create work that is output, for example, to power a generator. [0003] After passing through the turbine portion, the hot gases flow into an exhaust frame. The exhaust frame may include an inner barrel supported to an outer barrel through one or more struts. The inner barrel may support an aft bearing for the turbomachine. The exhaust gases passing through the exhaust frame flow to an exhaust stack prior to being discharged to ambient. Cooling fluid, generally compressor air, passes through the exhaust frame to cool the aft bearing. The cooling fluid also cools internal and external surfaces of the exhaust frame. The cooling fluid may pass from the exhaust frame into the exhaust gases or may be discharged directly to ambient.

BRIEF DESCRIPTION OF THE INVENTION [0004] According to one aspect of an exemplary embodiment, a turbomachine exhaust frame includes a body having an outer barrel member including an outer surface, an inner surface, and an inner barrel member having an outer surface and an inner surface. A first flow passage is defined by the outer surface and the inner surface of the outer barrel member and a second flow passage is defined by the outer surface and the inner surface of the inner barrel member. A first cooling circuit having a first inlet and a first outlet is fluidically connected to the first flow passage, and a second cooling circuit having a second inlet and a second outlet is fluidically connected to the second flow passage. At least one nozzle is arranged in the first flow passage and is fluidically connected to the first cooling circuit. The at least one nozzle includes at least one outlet arranged generally perpendicularly relative to the outer surface. The at least one nozzle is configured to introduce a fluid flow into the first flow passage in at least one of an axial direction and an annular direction. [0005] According to another aspect of the exemplary embodiment, a turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes an outlet. A combustor assembly includes at least one combustor fluidically connected to the compressor portion and the turbine portion, and an exhaust frame is operatively connected to the outlet of the turbine portion. The exhaust frame includes a body having an outer barrel member including an outer surface and an inner surface and an inner barrel member having an outer surface and an inner surface. A first flow passage is defined by the outer surface and the inner surface of the outer barrel member, and a second flow passage is defined by the outer surface and the inner surface of the inner barrel member. A first cooling circuit having a first inlet and a first outlet is fluidically connected to the first flow passage, and a second cooling circuit having a second inlet and a second outlet is fluidically connected to the second flow passage. At least one nozzle is arranged in the first flow passage and is fluidically connected to the first cooling circuit. The at least one nozzle includes at least one outlet arranged generally perpendicularly relative to the outer surface. The at least one nozzle is configured to introduce a fluid flow into the first flow passage in at least one of an axial direction and an annular direction.

[0006] According to yet another aspect of an exemplary embodiment, a turbomachine system includes a compressor portion having an inlet section, and a turbine portion operatively connected to the compressor portion. The turbine portion includes an outlet. A combustor assembly includes at least one combustor fluidically connected to the compressor portion and the turbine portion. An inlet system is fluidically connected to the inlet section. A mechanical system is operatively connected to one of the compressor portion and the turbine portion. An exhaust frame is operatively connected to the outlet of the turbine portion. The exhaust frame includes a body having an outer barrel member including an outer surface and an inner surface and an inner barrel member having an outer surface and an inner surface. A first flow passage is defined by the outer surface and the inner surface of the outer barrel member, and a second flow passage is defined by the outer surface and the inner surface of the inner barrel member. A first cooling circuit having a first inlet and a first outlet is fluidically connected to the first flow passage, and a second cooling circuit having a second inlet and a second outlet is fluidically connected to the second flow passage. At least one nozzle is arranged in the first flow passage and is fluidically connected to the first cooling circuit. The at least one nozzle includes at least one outlet arranged generally perpendicularly relative to the outer surface. The at least one nozzle is configured to introduce a fluid flow into the first flow passage in at least one of an axial direction and an annular direction.

[0007] These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.

BRIEF DESCRIPTION OF DRAWINGS [0008] The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which: [0009] FIG. 1 is a partial cross-sectional schematic view of a turbomachine system including an exhaust frame, in accordance with an exemplary embodiment;

[0010] FIG. 2 is perspective view of the exhaust frame of FIG. 1 ;

[001 1] FIG. 3 is a partial plan view of a nozzle mounted in an outer barrel of the exhaust frame of FIG. 2; and [0012] FIG. 4 is an exploded view of the nozzle and exhaust frame of FIG. 3.

[0013] The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings. DETAILED DESCRIPTION OF THE INVENTION

[0014] A turbomachine system, in accordance with an exemplary embodiment, is indicated generally at 2, in FIG. 1. Turbomachine system 2 includes a turbomachine 4 having a compressor portion 6 fluidically linked to a turbine portion 8 through a combustor assembly 10. Combustor assembly 10 includes one or more combustors 12. A shaft 14 operatively. connected to compressor portion 6 with turbine portion 8. Compressor portion 6 includes an inlet section 17 that is fluidically connected to an intake system 20. Intake system 20 may pre-condition air passing to compressor portion 6. For example, intake system 20 may dehumidify air passing to inlet section 17. Intake system 20 may also adjust flow parameters of the air passing to inlet section 17. Compressor portion 6 is also shown to be linked to a mechanical system 24. Mechanical system 24 may take the form of a generator 28. Of course, mechanical system 24 may take on other forms such as pumps and the like. Further, mechanical system 24 may be connected to turbine portion 8 in lieu of a connection to compressor portion 6. Turbine portion 8 includes an outlet 30 that is fluidically connected to an exhaust frame 40. Exhaust frame 40 conditions exhaust gases passing from outlet 30 prior to being passed to an exhaust stack (not shown), a heat recovery steam generator (HRSG) (also not shown) or other device.

[0015] In accordance with an exemplary embodiment illustrated in FIG. 2, exhaust frame 40 includes a body 44 having an outer barrel member 50 and an inner barrel member 52. Outer barrel member 50 includes an outer surface 57 that forms part of an outer casing (not separately labeled) for turbomachine 2 and an inner surface 58 (FIG. 1). Inner surface 58 may include an insulated or an un-insulated diffuser (not separately labeled). A first flow passage 61 is defined by outer surface 57 and inner surface 58 of outer barrel member 50. Inner barrel member 52 includes an outer surface 64 that may form part of the insulated or un-insulated diffuser and an inner surface 65 (FIG. 1). Inner barrel member 52 supports an aft bearing (not separately labeled) of turbomachine 2. It should be understood that inner barrel member may alternatively take the form of the aft bearing. A second flow passage 68 extends between outer surface 64 and inner surface 65. A plurality of struts, one of which is indicated at 70, extend between outer barrel member 50 and inner barrel member 52. Each strut 70 includes an inner passage 71 (FIG. 1) that is fluidically connected to second flow passage 68. First and second flow passages 61 and 68 deliver a cooling fluid to portions of exhaust frame 40. A portion of the cooling fluid may mix with the exhaust gases passing from outlet 30. [0016] In further accordance with an exemplary embodiment, exhaust frame 40 is fluidically connected to a fluid delivery system 74. Fluid delivery system 74 includes a fluid source 80 which may take the form of a blower 82. Fluid source 80 may also take the form of a connection to a compressor extraction or other source of fluid having a motive force. Fluid delivery system 74 includes a supply conduit 86 extending between fluid source 80 and exhaust frame 40. Supply conduit 86 includes a first cooling circuit 91 fluidically associated with outer barrel member 50 and a second, distinct, cooling circuit 94 fluidically associated with inner barrel member 52.

[0017] First cooling circuit 91 includes a first inlet 97 fluidically connected to supply conduit 86 and a first outlet 98 fluidically connected to first flow passage 61, as will be detailed below. Second cooling circuit 94 includes a second inlet 100 and a second outlet 102. Second inlet 100 is fluidically connected to supply conduit 86 and second outlet 102 is directly fluidically connected to second flow passage 68. In contrast, first cooling circuit 91 is connected to first flow passage 61 through a coolant delivery manifold 108 that extends annularly about, and is spaced from, outer barrel member 50. A plurality of fluid delivery conduits 113 extend between coolant delivery manifold 108 and second flow passage 68. A valve 116 is arranged in first cooling circuit 91 upstream of coolant delivery manifold 108. Valve 1 16 selectively fluidically disconnects second flow passage 68 from fluid source 80.

[0018] As shown in FIG. 3, each fluid delivery conduit 113 extends from a first end 122 fluidically connected to coolant delivery manifold 108, to a second end 123. Second end 123 is fluidically connected to a nozzle 130 which, as will become more readily apparent below, delivers a flow of coolant into first flow passage 61. The coolant may flow axially and/or annularly about outer barrel member 50, as will become more readily apparent below. As show in FIG. 2, a plurality of nozzles 130 is arranged about exhaust frame 40. Each nozzle 130 includes a body portion 140 having an interior zone 141. Body portion 140 extends from a first end section 142, defining an inlet 143, to a second end section 144 having an end cap 145. Nozzle 130 includes a plurality of outlets 146 arranged on body portion 140 between first and second end sections 142 and 144. Outlets 146 may be arranged to deliver an axial flow of fluid, an annular flow of fluid, and/or a combination of axial and annular flows depending upon desired cooling characteristics. Nozzle 130 also includes a flange 150 arranged at first end section 142. Flange 150 nests within a recess 154 formed in outer surface 57 of outer barrel member 50. Flange 150 includes a plurality of openings, one of which is indicated at 157, that receive corresponding mechanical fasteners 160. Mechanical fasteners 160 secure nozzles 130 to outer barrel member 50 and also facilitate replacement and/or repair as necessary.

[0019] In the exemplary embodiment shown, each of the plurality of outlets 146 take the form of oblong openings 167 having first and second generally linear side portions 171 and 173 joined by first and second curvilinear end portions 175 and 177. Of course it should be understood that the particular geometry of outlets 146 may vary. Outlets 146 deliver a flow of cooling fluid into first fluid passage 61. The delivery of fluid reduces temperatures in outer barrel member 50 while reducing the occurrence of thermal gradients in exhaust frame 40. Further, the use of first and second cooling circuits 91 and 94 provides additional control over cooling fluid through exhaust frame 40. Additionally, the selective control of cooling fluid into exhaust frame 40 allows operators to tailor fluid delivery in order to lower thermal loading of struts 70 that may extend between the outer and inner barrel members 50 and 52.

[0020] While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.

Claims

WHAT IS CLAIMED IS:

1. A turbomachine exhaust frame comprising: a body having an outer barrel member having an outer surface and an inner surface and an inner barrel member having an outer surface and an inner surface; a first flow passage defined by the outer surface and the inner surface of the outer barrel member and a second flow passage defined by the outer surface and the inner surface of the inner barrel member; a first cooling circuit having a first inlet and a first outlet fluidically connected to the first flow passage; a second cooling circuit having a second inlet and a second outlet fluidically connected to the second flow passage; and at least one nozzle arranged in the first flow passage and fluidically connected to the first cooling circuit, the at least one nozzle including at least one outlet arranged generally perpendicularly relative to the outer surface, the at least one nozzle being configured to introduce a fluid flow into the first flow passage in at least one of an axial and an annular direction.

2. The turbomachine exhaust frame according to claim 1, wherein the at least one nozzle includes a plurality of nozzles extending annularly about the outer barrel member.

3. The turbomachine exhaust frame according to claim 2, further comprising: a coolant delivery manifold fluidically connected to each of the plurality of nozzles.

4. The turbomachine exhaust frame according to claim 3, wherein the coolant delivery manifold is external of the body.

5. The turbomachine exhaust frame according to claim 1, wherein the at least one outlet includes a plurality of outlets arranged annularly about the at least one nozzle.

6. The turbomachine exhaust frame according to claim 5, wherein each of the plurality of outlets is defined by a generally oblong opening.

7. The turbomachine exhaust frame according to claim 1, further comprising: a strut extending between the outer surface of the inner barrel member and the inner surface of the outer barrel member, the strut including an internal cooling passage fluidically connected to the second cooling circuit.

8. The turbomachine exhaust frame according to claim 1, further comprising: a fluid delivery system and a valve arranged in the first cooling circuit, the valve being configured to selectively fluidically disconnect the at least one nozzle from the fluid delivery system.

9. The turbomachine exhaust frame according to claim 8, wherein the fluid delivery system comprises a blower configured to direct a flow of air into the first and second cooling circuits.

10. The turbomachine exhaust frame according to claim 1, further comprising: at least one opening extending through the outer surface of the outer barrel member, the at least one opening being fluidically connected to the first flow passage, a recess formed in the outer surface surrounds the at least one opening, the at least one nozzle including a flange nested in the recess.

1 1. A turbomachine comprising: a compressor portion; a turbine portion operatively connected to the compressor portion, the turbine portion including an outlet; a combustor assembly including at least one combustor fluidically connected to the compressor portion and the turbine portion; and an exhaust frame operatively connected to the outlet of the turbine portion, the exhaust frame comprising: a body having an outer barrel member having an outer surface and an inner surface and an inner barrel member having an outer surface and an inner surface; a first flow passage defined by the outer surface and the inner surface of the outer barrel member and a second flow passage defined by the outer surface and the inner surface of the inner barrel member; a first cooling circuit having a first inlet and a first outlet fluidically connected to the first flow passage; a second cooling circuit having a second inlet and a second outlet fluidically connected to the second flow passage; and at least one nozzle arranged in the first flow passage and fluidically connected to the first cooling circuit, the at least one nozzle including at least one outlet arranged generally perpendicularly relative to the outer surface, the at least one nozzle being configured to introduce a fluid flow into the first flow passage in at least one of an axial and an annular direction.

12. The turbomachine according to claim 11, wherein the at least one nozzle includes a plurality of nozzles extending annularly about the outer barrel member.

13. The turbomachine according to claim 12, further comprising: a coolant delivery manifold fluidically connected to each of the plurality of nozzles.

14. The turbomachine according to claim 13, wherein the coolant delivery manifold is external of the body.

15. The turbomachine according to claim 1 1 further comprising: a fluid delivery system and a valve arranged in the first cooling circuit, the valve being configured to selectively fluidically disconnect the at least one nozzle from the fluid delivery system.

16. The turbomachine according to claim 15, wherein the fluid delivery system comprises a blower configured to direct a flow of air into the first and second cooling circuits.

17. The turbomachine according to claim 11 further comprising: at least one opening extending through the outer surface of the outer barrel member, the at least one opening being fluidically connected to the first flow passage, a recess formed in the outer surface surrounds the at least one opening, the at least one nozzle including a flange nested in the recess.

18. A turbomachine system comprising: a compressor portion including an inlet section; a turbine portion operatively connected to the compressor portion, the turbine portion including an outlet; a combustor assembly including at least one combustor fluidically connected to the compressor portion and the turbine portion; an inlet system fluidically connected to the inlet section of the compressor portion; a mechanical system operatively connected to one of the turbine portion and the compressor portion; and an exhaust frame operatively connected to the outlet of the turbine portion, the exhaust frame comprising: a body having an outer barrel member having an outer surface and an inner surface and an inner barrel member having an outer surface and an inner surface; a first flow passage defined by the outer surface and the inner surface of the outer barrel member and a second flow passage defined by the outer surface and the inner surface of the inner barrel member; a first cooling circuit having a first inlet and a first outlet fluidically connected to the first flow passage; a second cooling circuit having a second inlet and a second outlet fluidically connected to the second flow passage; and at least one nozzle arranged in the first flow passage and fluidically connected to the first cooling circuit, the at least one nozzle including at least one outlet arranged generally perpendicularly relative to the outer surface, the at least one nozzle being configured to introduce a fluid flow into the first flow passage in at least one of an axial and an annular direction.

19. The turbomachine system according to claim 18, wherein the at least one nozzle includes a plurality of nozzles extending annularly about the outer barrel member.

20. The turbomachine system according to claim 19, further comprising: a coolant delivery manifold fluidically connected to each of the plurality of nozzles, the coolant delivery manifold being external of the body.