Turbomachinery exhaust casing

Abstract

Turbomachinery exhaust casing (40) comprising: a body having an outer sleeve member (50) with an outer surface (57) and an inner surface (58) and an inner sleeve member (52) with an outer surface (64) and an inner surface (65); a first flow passage (61) formed by the outer surface (57) and the inner surface (58) of the outer sleeve member (50) and a second flow passage (68) formed by the outer surface (64) and the inner surface (65) of the inner sleeve member (52); a first cooling circuit (91) having a first inlet (97) and a first outlet (98) fluidly connected to the first flow passage (61); a second cooling circuit (94) having a second inlet (100) and a second outlet (102) fluidly connected to the second flow passage (68); and at least one nozzle (130) arranged in the first flow passage (61) and fluidly connected to the first cooling circuit (91), wherein the at least one nozzle (130) has a plurality of outlets (146) arranged substantially at right angles relative to the outer surface (57) of the outer sleeve member (50), wherein the nozzle (130) includes a body portion (140) extending from a first end portion (142) to a second end portion (144) with an end cap (145), wherein a plurality of outlets (146) are arranged on the body portion (140) between the first and second end portions (142, 144) such that a fluid flow is introduced into the first flow passage (61) in an axial direction and / or a circumferential direction.

Description

BACKGROUND OF THE INVENTION

[0001] The subject matter disclosed herein relates to the field of turbomachinery, and more particularly to a turbomachinery exhaust casing.

[0002] Turbomachines include a compressor section connected to a turbine section via a common compressor / turbine shaft, and a combustor assembly. An inlet airflow is passed through an air inlet to the compressor section. In the compressor section, the inlet airflow is compressed through a number of successive stages to the combustor assembly. In the combustor assembly, the compressed airflow mixes with a fuel to form a combustible mixture. The combustible mixture is burned in the combustor assembly to form hot gases. The hot gases are passed along a hot gas path of the turbine section through a transition piece. The hot gases expand through a number of turbine stages and act on turbine blades mounted on wheels to produce work, which is output, for example, to drive a generator.

[0003] After passing through the turbine section, the hot gases flow into an exhaust casing. The exhaust casing may have an inner sleeve supported against an outer sleeve by one or more struts. The inner sleeve may support an aft bearing for the turbomachinery. The exhaust gases passing through the exhaust casing flow to an exhaust stack before being exhausted to the atmosphere. Cooling fluid, generally compressor air, passes through the exhaust casing to cool the aft bearing. The cooling fluid also cools internal and external surfaces of the exhaust casing. The cooling fluid may pass from the exhaust casing into the exhaust gases or may be exhausted directly to the atmosphere.

[0004] EP 2 497 907 A2 discloses a turbomachine exhaust casing in which struts extend between an inner structure and an outer structure. Cooling air can be guided through the struts. The cooling air can first be introduced from the outer structure through the struts into the inner structure, circulate there, and then exit through an outer flow channel through the struts. Cooling of struts is also described in EP 2 578 816 A2, EP 1 512 844 A2, and EP 2 261 468 A1.

[0005] EP 1 489 265 A2 describes a turbine nozzle arrangement. The nozzle arrangement is formed by turbine blades arranged circumferentially around the turbine. These turbine blades are cooled by cooling air supplied from a cooling air distributor into cooling passages within the blades. The design therefore relates to the turbine section of a turbine arranged upstream of an exhaust section. A similar arrangement is known from EP 1 621 734 A1. BRIEF DESCRIPTION OF THE INVENTION

[0006] The invention relates to a turbomachine exhaust casing with the features of patent claim 1. It has a body with an outer sleeve element having an outer surface and an inner surface, and with an inner sleeve element having an outer surface and an inner surface. A first flow passage is formed by the outer surface and the inner surface of the outer sleeve element, and a second flow passage is formed by the outer surface and the inner surface of the inner sleeve element. A first cooling circuit with a first inlet and a first outlet is fluidly connected to the first flow passage, and a second cooling circuit with a second inlet and a second outlet is fluidly connected to the second flow passage. At least one nozzle is arranged in the first flow passage and is fluidly connected to the first cooling circuit.The at least one nozzle includes at least one outlet arranged substantially perpendicular to the outer surface. The at least one nozzle is configured to introduce a fluid flow into the first flow passage in an axial direction and / or a circumferential direction.

[0007] The invention also relates to a turbomachine having the features of claim 11. It has a compressor section and a turbine section operatively connected to the compressor section. The turbine section includes an outlet. A combustor assembly includes at least one combustion chamber fluidly connected to the compressor section and the turbine section, and an exhaust casing is operatively connected to the outlet of the turbine section. The exhaust casing includes a body having an outer sleeve member having an outer surface and an inner surface and an inner sleeve member having an outer surface and an inner surface. A first flow passage is formed by the outer surface and the inner surface of the outer sleeve member, and a second flow passage is formed by the outer surface and the inner surface of the inner sleeve member.A first cooling circuit having a first inlet and a first outlet is fluidly connected to the first flow passage, and a second cooling circuit having a second inlet and a second outlet is fluidly connected to the second flow passage. At least one nozzle is arranged in the first flow passage and fluidly connected to the first cooling circuit. The at least one nozzle includes at least one outlet arranged substantially perpendicular to the outer surface. The at least one nozzle is configured to introduce a fluid flow into the first flow passage in an axial direction and / or a circumferential direction.

[0008] The invention also relates to a turbomachinery system having the features of claim 18. It has a compressor section with an inlet section and a turbine section operatively connected to the compressor section. The turbine section includes an outlet. A combustor assembly includes at least one combustion chamber fluidly connected to the compressor section and the turbine section. An inlet system is fluidly connected to the inlet section. A mechanical system is operatively connected to one of the compressor section and the turbine section. An exhaust housing is operatively connected to the outlet of the turbine section. The exhaust housing includes a body having an outer sleeve member having an outer surface and an inner surface and an inner sleeve member having an outer surface and an inner surface.A first flow passage is formed by the outer surface and the inner surface of the outer sleeve member, and a second flow passage is formed by the outer surface and the inner surface of the inner sleeve member. A first cooling circuit having a first inlet and a first outlet is fluidly connected to the first flow passage, and a second cooling circuit having a second inlet and a second outlet is fluidly connected to the second flow passage. At least one nozzle is arranged in the first flow passage and is fluidly connected to the first cooling circuit. The at least one nozzle includes at least one outlet arranged substantially perpendicular to the outer surface. The at least one nozzle is configured to introduce a fluid flow into the first flow passage in an axial direction and / or a circumferential direction.

[0009] These and other advantages and features will become more clearly understood from the following description taken in conjunction with the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] The subject matter regarded as the invention is particularly pointed out and distinctly claimed in the claims at the end of the specification. The foregoing and other features and advantages of the invention will become more apparent from the following detailed description taken in conjunction with the accompanying drawings, in which: Fig. 1 is a schematic, partially sectioned view of a turbomachinery system including an exhaust casing in accordance with an exemplary embodiment; Fig. 2 a perspective view of the exhaust housing from Fig. 1 is; Fig. 3 is a partial plan view of a nozzle mounted in an outer sleeve of the exhaust housing of Fig. 2 is attached; and Fig. 4 an exploded view of the nozzle and the exhaust housing from Fig. 3 is.

[0011] 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

[0012] A turbomachinery system in accordance with an exemplary embodiment is generally described in Fig. 1 at 2. The turbomachinery system 2 includes a turbomachine 4 having a compressor section 6 fluidly coupled to a turbine section 8 via a combustor assembly 10. The combustor assembly 10 includes one or more combustion chambers 12. A shaft 14 is operatively connected between the compressor section 6 and the turbine section 8. The compressor section 6 includes an inlet section 17 fluidly connected to an inlet system 20. The inlet system 20 can precondition air passing to the compressor section 6. For example, the inlet system 20 can dehumidify air passing to the inlet section 17. The inlet system 20 can also adjust flow parameters of the air passing to the inlet section 17. The compressor section 6 is also shown coupled to a mechanical system 24. The mechanical system 24 can take the form of a generator 28.Of course, the mechanical system 24 may take other forms, such as pumps or the like. Furthermore, the mechanical system 24 may be connected to the turbine section 8 instead of being connected to the compressor section 6. The turbine section 8 includes an outlet 30 fluidly connected to an exhaust housing 40. The exhaust housing 40 conditions exhaust gases emerging from the outlet 30 before they reach an exhaust duct (not shown), a heat recovery steam generator (HRSG) (also not illustrated), or other facilities.

[0013] In accordance with a Fig. 2, the exhaust housing 40 is connected to the body 44 with an outer sleeve member 50 and an inner sleeve member 52. The outer sleeve member 50 includes an outer surface 57 which is part of an outer casing (not separately labeled) for the turbomachine 2 and an inner surface 58 ( Fig. 1). The inner surface 58 may include an insulated or non-insulated diffuser (not separately labeled). A first flow passage 61 is formed by the outer surface 57 and the inner surface 58 of the outer sleeve member 50. The inner sleeve member 52 includes an outer surface 64, which may be part of an insulated or non-insulated diffuser, and an inner surface 65 ( Fig. 1). The inner sleeve member 52 supports a rear bearing (not separately labeled) of the turbomachine 2. It should be understood that the inner sleeve member may alternatively have the shape of the rear bearing. A second flow passage 68 extends between the outer surface 64 and the inner surface 65. A plurality of struts, one of which is designated 70, extends between the outer sleeve member 50 and the inner sleeve member 52. Each strut 70 includes an internal passage 71 ( Fig. 1), which is fluidly connected to the second flow passage 68. The first and second flow passages 61 and 68 supply a cooling fluid to portions of the exhaust housing 40. A portion of the cooling fluid may mix with the exhaust gases coming from the outlet 30.

[0014] In further accordance with an exemplary embodiment, the exhaust housing 40 is fluidly connected to a fluid distribution system 74. The fluid distribution system 74 includes a fluid source 80, which may take the form of a fan 82. The fluid source 80 may also take the form of a connection to a compressor exhaust or other source of fluid with a motive force. The fluid distribution system 74 includes a supply channel 86 extending between the fluid source 80 and the exhaust housing 40. The supply channel 86 includes a first cooling circuit 91 fluidly connected to the outer sleeve member 60 and a second, separate cooling circuit 94 fluidly connected to the inner sleeve member 52.

[0015] The first cooling circuit 91 includes a first inlet 97 fluidly connected to the supply channel 86 and a first outlet 98 fluidly connected to the first flow passage 61, as detailed below. The second cooling circuit 94 includes a second inlet 100 and a second outlet 102. The second inlet 100 is fluidly connected to the supply channel 86, and the second outlet 102 is directly fluidly connected to the second flow passage 68. In contrast, the first cooling circuit 91 is connected to the first flow passage 61 via a coolant manifold 108 that extends circumferentially around the outer sleeve member 50 and is spaced from the outer sleeve member 50. A plurality of fluid distribution channels 113 extend between the coolant distributor 108 and the second flow passage 68. A valve 116 is arranged in the first cooling circuit 91 upstream of the coolant distributor 108.The valve 116 selectively fluidically separates the second flow passage 68 from the fluid source 80.

[0016] As it is in Fig. 3, each fluid distribution channel 113 extends from a first end 122, which is fluidly connected to the coolant manifold 108, to a second end 123. The second end 123 is fluidly connected to a nozzle 130, which, as will become more readily apparent below, discharges a flow of coolant into the first flow passage 61. The coolant may flow axially and / or circumferentially around the outer sleeve member 50, as will become more readily apparent below. As shown in Fig.2, a plurality of nozzles 130 are arranged around the exhaust housing 40. Each nozzle 130 includes a body portion 140 having an interior zone 141. The body portion 140 extends from a first end portion 142 defining an inlet 143 to a second end portion 144 having an end cap 145. The nozzle 130 includes a plurality of outlets 146 disposed on the body portion 140 between the first and second end portions 142 and 144. The outlets 146 may be arranged to deliver an axial flow of fluid, a circumferential flow of fluid, and / or a combination of axial and circumferential flow, depending on the desired cooling characteristics. The nozzle 130 also includes a flange 150 disposed on the first portion 142. The flange 150 lies in a recess 154 formed in the outer surface 57 of the outer sleeve member 50.The flange 150 includes a plurality of openings, one of which is designated 157, which receive corresponding mechanical fasteners 160. The mechanical fasteners 160 secure the nozzles 130 to the outer sleeve member 50 and also allow for replacement and / or repair as needed.

[0017] In the illustrated exemplary embodiment, each of the plurality of outlets 146 is in the form of an elongated opening 167 having substantially first and second linear side portions 171 and 173 connected by first and second curved end portions 175 and 177. Of course, it should be understood that the particular geometry of the outlets 146 may vary. The outlets 146 discharge a flow of cooling fluid into the first fluid passage 61. The discharge of fluid reduces temperatures within the outer sleeve member 50 while reducing the occurrence of thermal gradients within the exhaust housing 40. Furthermore, the use of first and second cooling circuits 91 and 94 provides additional control over the cooling fluid through the exhaust housing 40.Additionally, the selective control of the cooling fluid into the exhaust housing 40 allows operators to tailor the fluid delivery to reduce the thermal loads on the struts 70 that may extend between the outer and inner sleeve members 50 and 52.

[0018] 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 may be modified to include a number of variations, alterations, substitutions, or equivalent arrangements not previously described, but which are within the spirit and scope of the invention. Furthermore, it should be understood that while various embodiments of the invention have been described, aspects of the invention include only some of the described embodiments. Accordingly, the invention is not to be considered limited by the foregoing description, but is only limited by the scope of the appended claims.

Claims

[1] Turbomachinery exhaust casing (40) comprising: a body having an outer sleeve member (50) with an outer surface (57) and an inner surface (58) and an inner sleeve member (52) with an outer surface (64) and an inner surface (65); a first flow passage (61) formed by the outer surface (57) and the inner surface (58) of the outer sleeve member (50) and a second flow passage (68) formed by the outer surface (64) and the inner surface (65) of the inner sleeve member (52); a first cooling circuit (91) having a first inlet (97) and a first outlet (98) fluidly connected to the first flow passage (61); a second cooling circuit (94) having a second inlet (100) and a second outlet (102) fluidly connected to the second flow passage (68); and at least one nozzle (130) arranged in the first flow passage (61) and fluidly connected to the first cooling circuit (91), wherein the at least one nozzle (130) has a plurality of outlets (146) arranged substantially at right angles relative to the outer surface (57) of the outer sleeve member (50), wherein the nozzle (130) includes a body portion (140) extending from a first end portion (142) to a second end portion (144) with an end cap (145), wherein a plurality of outlets (146) are arranged on the body portion (140) between the first and second end portions (142, 144) such that a fluid flow is introduced into the first flow passage (61) in an axial direction and / or a circumferential direction. [2] A turbomachine exhaust casing according to claim 1, wherein there are a plurality of nozzles (130) arranged circumferentially around the outer sleeve member (50). [3] The turbomachine exhaust housing of claim 2, further comprising: a coolant manifold (108) fluidly connected to each of the plurality of nozzles (130). [4] The turbomachine exhaust housing of claim 3, wherein the coolant manifold (108) is disposed outside the body portion (140). [5] Turbomachinery exhaust casing according to claim 1, wherein the outlets (146) are arranged annularly around the at least one nozzle (130). [6] The turbomachinery exhaust casing of claim 5, wherein each of the outlets (146) is formed by a substantially elongated opening. [7] The turbomachinery exhaust casing of claim 1, further comprising: a strut (70) extending between the outer surface (64) of the inner sleeve member (52) and the inner surface (58) of the outer sleeve member (50), the strut (70) having an internal cooling passage (71) fluidly connected to the second cooling circuit (94). [8] The turbomachine exhaust casing of claim 1, further comprising: a fluid distribution system (74) and a valve (116) disposed in the first cooling circuit (91), wherein the valve (116) is configured to selectively fluidically isolate the at least one nozzle (130) from the fluid distribution system (74). [9] The turbomachine exhaust housing of claim 8, wherein the fluid distribution system (74) includes a fan (82) configured to direct air flow into the first and second cooling circuits (91, 94). [10] The turbomachine exhaust casing of claim 1, further comprising: at least one opening extending through the outer surface of the outer sleeve member (50), the at least one opening (157) fluidly connected to the first flow passage (61); a recess (154) formed in the outer surface (57) and enclosing the at least one opening (157), the at least one nozzle (130) having a flange (150) located in the recess. [11] Turbomachine (4) comprising: a compressor section (6); a turbine section (8) operatively connected to the compressor section (6), the turbine section (8) having an outlet; a combustion chamber arrangement (10) having at least one combustion chamber (12) fluidly connected to the compressor section (6) and the turbine section (8); and an exhaust housing (40) operatively connected to the outlet of the turbine section (8), the exhaust housing (40) comprising: a body having an outer sleeve member (50) with an outer surface (57) and an inner surface (58) and an inner sleeve member (52) with an outer surface (64) and an inner surface (65); a first flow passage (61) formed by the outer surface (57) and the inner surface (58) of the outer sleeve member (50) and a second flow passage (68) formed by the outer surface (64) and the inner surface (65) of the inner sleeve member (52); a first cooling circuit (91) having a first inlet (97) and a first outlet (98) fluidly connected to the first flow passage (61); a second cooling circuit (94) having a second inlet (100) and a second outlet (102) fluidly connected to the second flow passage (68); and at least one nozzle (130) arranged in the first flow passage (61) and fluidly connected to the first cooling circuit (91), wherein the at least one nozzle (130) has a plurality of outlets (146) arranged substantially perpendicular to the outer surface (57) of the outer sleeve member (50), wherein the nozzle (130) includes a body portion (140) extending from a first end portion (142) to a second end portion (144) with an end cap (145), wherein a plurality of outlets (146) are arranged on the body portion (140) between the first and second end portions (142, 144) such that a fluid flow is introduced into the first flow passage (61) in an axial direction and / or a circumferential direction. [12] Turbomachine according to claim 11, wherein the plurality of nozzles (130) are arranged annularly around the outer sleeve member (50). [13] The turbomachine of claim 12, further comprising: a coolant manifold (108) fluidly connected to each of the plurality of nozzles (130). [14] Turbomachine according to claim 13, wherein the coolant distributor (108) is arranged outside the body. [15] The turbomachine of claim 11, further comprising: a fluid distribution system (74) and a valve (116) disposed in the first cooling circuit (91), wherein the valve (116) is configured to selectively fluidically isolate the at least one nozzle (130) from the fluid distribution system (74). [16] Turbomachine according to claim 15, wherein the fluid distribution system (74) comprises a fan (82) configured to direct an air flow into the first and second cooling circuits (91, 94). [17] The turbomachine of claim 11, further comprising: at least one opening extending through the outer surface (57) of the outer sleeve member (50), the at least one opening being fluidly connected to the first flow passage (61); a recess (154) formed in the outer surface (57) and enclosing the at least one opening (157), the at least one nozzle (130) having a flange (150) located in the recess (154). [18] Turbomachinery system (2) comprising: a compressor section (6) having an inlet section (17); a turbine section (8) operatively connected to the compressor section (6), the turbine section (8) having an outlet; a combustion chamber arrangement (10) comprising at least one combustion chamber (12) which is fluidly connected to the compressor section (6) and the turbine section (8); an inlet system (20) fluidly connected to the inlet section (17) of the compressor section (6); a mechanical system operatively connected to the turbine section (8) or the compressor section (6); and a turbomachine exhaust casing (40) operatively connected to the outlet of the turbine section (8), the turbomachine exhaust casing (40) comprising: a body comprising an outer sleeve member (50) having an outer surface (57) and an inner surface (58) and an inner sleeve member (52) having an outer surface (64) and an inner surface (65); a first flow passage (61) formed by the outer surface (57) and the inner surface (58) of the outer sleeve member (50) and a second flow passage (68) formed by the outer surface (64) and the inner surface (65) of the inner sleeve member (52); a first cooling circuit (91) having a first inlet (97) and a first outlet (98) fluidly connected to the first flow passage (61); a second cooling circuit (94) having a second inlet (100) and a second outlet (102) fluidly connected to the second flow passage (68); and at least one nozzle (130) arranged in the first flow passage (61) and fluidly connected to the first cooling circuit (91), wherein the at least one nozzle (130) has a plurality of outlets (146) arranged substantially perpendicular to the outer surface (57) of the outer sleeve member (50), wherein the nozzle (130) includes a body portion (140) extending from a first end portion (142) to a second end portion (144) with an end cap (145), wherein a plurality of outlets (146) are arranged on the body portion (140) between the first and second end portions (142, 144) such that a fluid flow is introduced into the first flow passage (61) in the axial direction and / or circumferential direction. [19] A turbomachinery system according to claim 18, wherein the nozzles (130) are arranged annularly around the outer sleeve member (50). [20] The turbomachinery system of claim 19, further comprising: a coolant manifold (108) fluidly connected to each of the nozzles (130), the coolant manifold (108) being disposed externally of the body.

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