WO2019194797A1 - Exhaust gas collector for a turbine - Google Patents

Exhaust gas collector for a turbine Download PDF

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Publication number
WO2019194797A1
WO2019194797A1 PCT/US2018/025979 US2018025979W WO2019194797A1 WO 2019194797 A1 WO2019194797 A1 WO 2019194797A1 US 2018025979 W US2018025979 W US 2018025979W WO 2019194797 A1 WO2019194797 A1 WO 2019194797A1
Authority
WO
WIPO (PCT)
Prior art keywords
collector
aperture
exhaust gas
turbine
stack
Prior art date
Application number
PCT/US2018/025979
Other languages
French (fr)
Inventor
Dennis Runyon
Jaskirat SINGH
Dipankar DUA
Anthony Saladino
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/US2018/025979 priority Critical patent/WO2019194797A1/en
Publication of WO2019194797A1 publication Critical patent/WO2019194797A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • aspects of the invention relate to an exhaust gas collector for a turbine, and more particularly, to an exhaust gas collector having a collector aperture whose shape is defined by first and second straight sections and first and second curved end sections wherein the first curved end section is located between first ends of the first and second straight sections and the second curved section is located between second ends of the first and second straight sections.
  • Gas turbine engines may be used to drive a load such as an electric generator connected to an electric distribution grid or turbomachinery such as a compressor or compressor train.
  • a gas turbine 26 is schematically shown.
  • the gas turbine 26 includes a compressor 28, which draws in ambient air 30 and delivers compressed air 32 to a combustor 34.
  • a fuel supply 36 delivers fuel 38 to the combustor 34 where it is combined with the compressed air 32 and the fuel 38 is burned to produce high temperature working gas 40.
  • the working gas 40 is expanded through a turbine section 42, which includes a series of rows of stationary vanes and rotating turbine blades. The working gas 40 causes the blades to rotate a turbine shaft 46 that drives the compressor 28.
  • a power turbine 48 having an output shaft 50 is located downstream from the turbine section 42.
  • the output shaft 50 is connected to a load 44.
  • the working gas 40 also flows through the power turbine 48 and is used to rotate the output shaft 50 to drive the load 44.
  • Hot exhaust gas 52 exits the power turbine 48 and enters an exhaust gas diffuser that reduces a velocity of the exhaust gas.
  • the exhaust gas 52 then enters an exhaust gas collector 54 and is subsequently vented to atmosphere via an exhaust stack 55 connected to the collector 54.
  • the collector 54 includes a collector aperture that enables a flow of exhaust gas 52 from the collector 54 to the exhaust stack 55.
  • Fig. 2 a top view of a conventional collector 54 is shown.
  • the collector 54 includes straight sections 56 connected in a rectangular shape having square corners 60 to form a substantially rectangular shaped collector aperture 58.
  • Each of the comers 60 forms a stress concentration area.
  • the collector 54 is subjected to high temperatures due to the hot exhaust gas, resulting in cyclic thermal expansion of the collector 54. This results in the undesirable formation of cracks (i.e. crack initiation and propagation) in the comers 60 of the collector 54, due to the stress concentration at the corners 60, which shortens product life.
  • An exhaust gas collector for a turbine that generates exhaust gas that flows along a first axis, wherein the exhaust gas is vented via an exhaust stack.
  • the collector includes first and second side walls separated by a circumferential wall to form a plenum that receives the exhaust gas from the turbine.
  • the first side wall includes a first aperture for receiving a portion of the turbine and the second side wall includes a second aperture that provides a clearance for an output shaft of the turbine.
  • the collector also includes a collector aperture formed in a top portion of the collector, wherein the collector aperture provides a flow path for the exhaust gas from the plenum to the exhaust stack.
  • a shape of the collector aperture is defined by first and second straight sections and first and second curved end sections wherein the first curved end section is located between first ends of the first and second straight sections and the second curved section is located between second ends of the first and second straight sections.
  • Fig. 1 is a schematic of a gas turbine that includes a power turbine.
  • Fig. 2 is a top view of an aperture of a conventional exhaust gas collector.
  • Fig. 3 is a perspective view of an exhaust gas collector in accordance with aspects of the invention.
  • Fig. 4 is a top view of the exhaust gas collector along view line 4-4 of Fig. 3.
  • Fig. 5 is a perspective view of an alternate embodiment of the exhaust gas collector.
  • Fig. 6 is a top view of the exhaust gas collector along view line 6-6 of Fig. 5.
  • Figs. 7A-7B are top and side views, respectively, of a transition piece.
  • a gas turbine 26 generates high temperature exhaust gas 52 that enters an exhaust gas diffuser which serves to reduce a velocity of the exhaust gas 52.
  • the exhaust gas 52 enters a collector and is subsequently vented to atmosphere via an exhaust stack 55 connected to the collector.
  • Fig. 3 a perspective view of an exhaust gas collector 62 in accordance with aspects of the invention is shown.
  • the collector 62 includes first 64 and second 66 side walls that are oriented substantially transverse or orthogonal to a first axis 68 of the collector 62.
  • the first axis 68 corresponds to a center axis of the output shaft 50 of the power turbine 48.
  • the first 64 and second 66 side walls are spaced apart from each other by an outer circumferential wall 70 oriented about the first axis 68.
  • the first side wall 64 includes a first aperture 72 that receives an exhaust gas diffuser of the gas turbine 26.
  • the first 64 and second 66 side walls and the circumferential wall 70 form a cavity or plenum 74 that receives exhaust gas 52 from the exhaust gas diffuser along the first axis 68.
  • the second side wall 66 includes a second aperture 76 that provides a pass- through clearance for the output shaft 50 of the power turbine 48 to enable attachment of the output shaft 50 to the load 44.
  • a top portion 78 of the collector 62 includes a collector aperture 80 that enables exhaust gas 52 to flow from the collector 62 to a transition piece 82 (see Figs. 5A and 5B) and ultimately to an exhaust stack 55.
  • the collector aperture 80 may be oriented substantially orthogonal or transverse to the first aperture 72 such that the flow of exhaust gas 52 is directed along a second axis 84 substantially orthogonal or transverse to the first axis 68.
  • the collector aperture 80 may be oriented in directions other than orthogonal to the first axis 68 to provide exhaust gas flow in other directions.
  • Fig. 4 is a top view of the collector 62 along view line 4-4 of Fig. 3.
  • a geometry or shape of the collector aperture 80 is formed by first 86 and second 88 straight sections that are spaced apart from each other to define a collector aperture width W.
  • the first straight section 86 includes first 86A and second 86B ends and the second straight section 88 includes third 88A and fourth 88B ends.
  • a first curved end section 90 is located between the first 86A and third 88A ends.
  • a second curved section 92 is located between the second 86B and fourth 88B ends to form a collector aperture 80 having a substantially“racetrack” shaped configuration.
  • the curved end sections 90, 92 are each defined by a corner radius R. It has been found that use of curved end sections 90, 92 substantially reduces areas of stress concentration in the collector structure forming the collector aperture 80, thus substantially reducing the occurrence of crack initiation and propagation in the collector 62 and substantially extending the product life of the collector 62.
  • the curved end sections 90, 92 also affect aerodynamic performance of the collector aperture 80, thus affecting the flow of exhaust gas 52 through the collector aperture 80.
  • the collector aperture 80 is configured to reduce areas of stress concentration in the collector 62 while simultaneously providing sufficient aerodynamic performance to enable suitable exhaust gas flow through the collector aperture 80.
  • a size ratio of the corner radius R relative to the aperture width W is used to configure the aperture 80. Further, the size ratio is selected to be within a predetermined range suitable for reducing areas of stress concentration in the collector aperture 80 while simultaneously providing sufficient aerodynamic performance. In accordance with aspects of the invention, the size ratio range is 0.1 to 0.41.
  • FIG. 6 is a top view of the collector 94 along view line 6-6 of Fig. 5.
  • the top portion 78 of the collector 94 includes a collector aperture 96 wherein a first end section 98 is located between the first 86A and third 88A ends and a second end section 100 is located between the second 86B and fourth 88B ends, respectively.
  • the first end section 98 includes an intermediate straight section, or first flat section 102, located between first 104 and second 106 curved sections.
  • the second end section 100 includes a second flat section 108 located between third 110 and fourth 112 curved sections.
  • the curved sections 104, 106, 110, 112 are each defined by a comer radius R. It has been found that use of curved sections 104, 106, 110, 112 substantially reduces areas of stress concentration in the collector structure forming the collector aperture 96, thus substantially reducing the occurrence of crack initiation and propagation in the collector 94 and substantially extending the product life of the collector 94.
  • the curved sections 104, 106, 110, 112 also affect aerodynamic performance of the collector aperture 96, thus affecting the flow of exhaust gas 52 through the collector aperture 96.
  • the collector aperture 96 is configured to reduce areas of stress concentration in the collector 94 while simultaneously providing sufficient aerodynamic performance to enable suitable exhaust gas flow through the collector aperture 96.
  • a size ratio of the comer radius R relative to the aperture width W is used to configure the aperture 98 as previously described. In an embodiment, the size ratio is 0.22 wherein the corner radius R may be approximately 12 in. and the aperture width may be approximately 53.59 in.
  • the transition piece 82 is located between a collector (i.e. between either collector 62, 94) and the exhaust stack 55 and provides an exhaust gas flow path from a collector 62, 94 to the exhaust stack 55.
  • the transition piece 82 includes a transition wall 114 having lower 116 and upper 118 wall portions.
  • the lower 116 and upper 118 wall portions include lower 120 and upper 122 apertures, respectively.
  • the lower portion 116 includes first 124 and second 126 straight sections connected by associated end sections corresponding to the first 98 and second 100 end sections such that the shape of the lower aperture 120 corresponds to the shape of the collector aperture 96.
  • the lower aperture 120 may have a shape corresponding to the collector aperture 80.
  • the shape of the upper aperture 122 corresponds to a shape of a stack aperture of the exhaust stack 55.
  • the upper aperture 122 may have a substantially round shape.
  • the upper aperture 122 of the transition piece 82 is configured to accommodate the size and shape of a stack aperture of the exhaust stack 55 and the lower aperture 120 of the transition piece 82 is configured to accommodate the size and shape of either the collector 80 or the collector 96. This enables attachment of the transition piece 82 to either collector 62 or collector 94 and the exhaust stack 55 to provide a flow path for the exhaust gas 52 that extends from either collector 62 or collector 94 to the exhaust stack 55.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

An exhaust gas collector (62) for a turbine (26) that generates exhaust gas (52). The collector (62) includes first (64) and second (66) side walls separated by a circumferential wall (70) to form a plenum (74) that receives the exhaust gas (52). The first side wall (64) includes a first aperture (72) for receiving a portion of the turbine (26) and the second side wall (66) includes a second aperture (76) that provides a clearance for an output shaft (50) of the turbine (26). The collector (62) also includes a collector aperture (80) that provides a flow path for the exhaust gas (52) from the plenum (74) to an exhaust stack (55). A shape of the collector aperture (80) is defined by first (86) and second (88) straight sections and first (90) and second (92) curved end sections. The first curved end section (90) is located between first ends (86A, 88B) of the first (86) and second (88) straight sections and the second curved section (92) is located between second ends (86B, 88B) of the first (86) and second (88) straight sections.

Description

EXHAUST GAS COLLECTOR FOR A TURBINE
BACKGROUND
1. Technical Field
Aspects of the invention relate to an exhaust gas collector for a turbine, and more particularly, to an exhaust gas collector having a collector aperture whose shape is defined by first and second straight sections and first and second curved end sections wherein the first curved end section is located between first ends of the first and second straight sections and the second curved section is located between second ends of the first and second straight sections.
2. Description of Related Art
Gas turbine engines may be used to drive a load such as an electric generator connected to an electric distribution grid or turbomachinery such as a compressor or compressor train. Referring to Fig. 1, a gas turbine 26 is schematically shown. The gas turbine 26 includes a compressor 28, which draws in ambient air 30 and delivers compressed air 32 to a combustor 34. A fuel supply 36 delivers fuel 38 to the combustor 34 where it is combined with the compressed air 32 and the fuel 38 is burned to produce high temperature working gas 40. The working gas 40 is expanded through a turbine section 42, which includes a series of rows of stationary vanes and rotating turbine blades. The working gas 40 causes the blades to rotate a turbine shaft 46 that drives the compressor 28. In an embodiment, a power turbine 48 having an output shaft 50 is located downstream from the turbine section 42. The output shaft 50 is connected to a load 44. In this application, the working gas 40 also flows through the power turbine 48 and is used to rotate the output shaft 50 to drive the load 44.
Hot exhaust gas 52 exits the power turbine 48 and enters an exhaust gas diffuser that reduces a velocity of the exhaust gas. The exhaust gas 52 then enters an exhaust gas collector 54 and is subsequently vented to atmosphere via an exhaust stack 55 connected to the collector 54. The collector 54 includes a collector aperture that enables a flow of exhaust gas 52 from the collector 54 to the exhaust stack 55. Referring to Fig. 2, a top view of a conventional collector 54 is shown. The collector 54 includes straight sections 56 connected in a rectangular shape having square corners 60 to form a substantially rectangular shaped collector aperture 58. Each of the comers 60 forms a stress concentration area. During use, the collector 54 is subjected to high temperatures due to the hot exhaust gas, resulting in cyclic thermal expansion of the collector 54. This results in the undesirable formation of cracks (i.e. crack initiation and propagation) in the comers 60 of the collector 54, due to the stress concentration at the corners 60, which shortens product life.
SUMMARY
An exhaust gas collector is disclosed for a turbine that generates exhaust gas that flows along a first axis, wherein the exhaust gas is vented via an exhaust stack. The collector includes first and second side walls separated by a circumferential wall to form a plenum that receives the exhaust gas from the turbine. The first side wall includes a first aperture for receiving a portion of the turbine and the second side wall includes a second aperture that provides a clearance for an output shaft of the turbine. The collector also includes a collector aperture formed in a top portion of the collector, wherein the collector aperture provides a flow path for the exhaust gas from the plenum to the exhaust stack. A shape of the collector aperture is defined by first and second straight sections and first and second curved end sections wherein the first curved end section is located between first ends of the first and second straight sections and the second curved section is located between second ends of the first and second straight sections.
Those skilled in the art may apply the respective features of the present invention jointly or severally in any combination or sub-combination.
BRIEF DESCRIPTION OF DRAWINGS
The exemplary embodiments of the invention are further described in the following detailed description in conjunction with the accompanying drawings, in which:
Fig. 1 is a schematic of a gas turbine that includes a power turbine. Fig. 2 is a top view of an aperture of a conventional exhaust gas collector.
Fig. 3 is a perspective view of an exhaust gas collector in accordance with aspects of the invention.
Fig. 4 is a top view of the exhaust gas collector along view line 4-4 of Fig. 3.
Fig. 5 is a perspective view of an alternate embodiment of the exhaust gas collector.
Fig. 6 is a top view of the exhaust gas collector along view line 6-6 of Fig. 5.
Figs. 7A-7B are top and side views, respectively, of a transition piece.
To facilitate understanding, identical reference numerals have been used, where possible, to designate identical elements that are common to the figures. The figures are not drawn to scale.
DETAILED DESCRIPTION
Although various embodiments that incorporate the teachings of the present disclosure have been shown and described in detail herein, those skilled in the art can readily devise many other varied embodiments that still incorporate these teachings. The scope of the disclosure is not limited in its application to the exemplary embodiment details of construction and the arrangement of components set forth in the description or illustrated in the drawings. The disclosure encompasses other embodiments and of being practiced or of being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting. The use of“including,”“comprising,” or“having” and variations thereof herein is meant to encompass the items listed thereafter and equivalents thereof as well as additional items. Unless specified or limited otherwise, the terms “mounted,” “connected,” “supported,” and“coupled” and variations thereof are used broadly and encompass direct and indirect mountings, connections, supports, and couplings. Further,“connected” and “coupled” are not restricted to physical or mechanical connections or couplings. A gas turbine 26 generates high temperature exhaust gas 52 that enters an exhaust gas diffuser which serves to reduce a velocity of the exhaust gas 52. The exhaust gas 52 enters a collector and is subsequently vented to atmosphere via an exhaust stack 55 connected to the collector. Referring to Fig. 3, a perspective view of an exhaust gas collector 62 in accordance with aspects of the invention is shown. The collector 62 includes first 64 and second 66 side walls that are oriented substantially transverse or orthogonal to a first axis 68 of the collector 62. The first axis 68 corresponds to a center axis of the output shaft 50 of the power turbine 48. The first 64 and second 66 side walls are spaced apart from each other by an outer circumferential wall 70 oriented about the first axis 68. The first side wall 64 includes a first aperture 72 that receives an exhaust gas diffuser of the gas turbine 26. The first 64 and second 66 side walls and the circumferential wall 70 form a cavity or plenum 74 that receives exhaust gas 52 from the exhaust gas diffuser along the first axis 68. The second side wall 66 includes a second aperture 76 that provides a pass- through clearance for the output shaft 50 of the power turbine 48 to enable attachment of the output shaft 50 to the load 44.
A top portion 78 of the collector 62 includes a collector aperture 80 that enables exhaust gas 52 to flow from the collector 62 to a transition piece 82 (see Figs. 5A and 5B) and ultimately to an exhaust stack 55. The collector aperture 80 may be oriented substantially orthogonal or transverse to the first aperture 72 such that the flow of exhaust gas 52 is directed along a second axis 84 substantially orthogonal or transverse to the first axis 68. In accordance with aspects of the invention, the collector aperture 80 may be oriented in directions other than orthogonal to the first axis 68 to provide exhaust gas flow in other directions.
Fig. 4 is a top view of the collector 62 along view line 4-4 of Fig. 3. In accordance with aspects of the invention, a geometry or shape of the collector aperture 80 is formed by first 86 and second 88 straight sections that are spaced apart from each other to define a collector aperture width W. The first straight section 86 includes first 86A and second 86B ends and the second straight section 88 includes third 88A and fourth 88B ends. A first curved end section 90 is located between the first 86A and third 88A ends. In addition, a second curved section 92 is located between the second 86B and fourth 88B ends to form a collector aperture 80 having a substantially“racetrack” shaped configuration. The curved end sections 90, 92 are each defined by a corner radius R. It has been found that use of curved end sections 90, 92 substantially reduces areas of stress concentration in the collector structure forming the collector aperture 80, thus substantially reducing the occurrence of crack initiation and propagation in the collector 62 and substantially extending the product life of the collector 62. The curved end sections 90, 92 also affect aerodynamic performance of the collector aperture 80, thus affecting the flow of exhaust gas 52 through the collector aperture 80. In accordance with aspects of the invention, the collector aperture 80 is configured to reduce areas of stress concentration in the collector 62 while simultaneously providing sufficient aerodynamic performance to enable suitable exhaust gas flow through the collector aperture 80. In particular, a size ratio of the corner radius R relative to the aperture width W is used to configure the aperture 80. Further, the size ratio is selected to be within a predetermined range suitable for reducing areas of stress concentration in the collector aperture 80 while simultaneously providing sufficient aerodynamic performance. In accordance with aspects of the invention, the size ratio range is 0.1 to 0.41.
Referring to Fig. 5, an alternate embodiment for an exhaust gas collector 94 is shown. Fig. 6 is a top view of the collector 94 along view line 6-6 of Fig. 5. In this embodiment, the top portion 78 of the collector 94 includes a collector aperture 96 wherein a first end section 98 is located between the first 86A and third 88A ends and a second end section 100 is located between the second 86B and fourth 88B ends, respectively. The first end section 98 includes an intermediate straight section, or first flat section 102, located between first 104 and second 106 curved sections. The second end section 100 includes a second flat section 108 located between third 110 and fourth 112 curved sections.
The curved sections 104, 106, 110, 112 are each defined by a comer radius R. It has been found that use of curved sections 104, 106, 110, 112 substantially reduces areas of stress concentration in the collector structure forming the collector aperture 96, thus substantially reducing the occurrence of crack initiation and propagation in the collector 94 and substantially extending the product life of the collector 94. The curved sections 104, 106, 110, 112 also affect aerodynamic performance of the collector aperture 96, thus affecting the flow of exhaust gas 52 through the collector aperture 96. In accordance with aspects of the invention, the collector aperture 96 is configured to reduce areas of stress concentration in the collector 94 while simultaneously providing sufficient aerodynamic performance to enable suitable exhaust gas flow through the collector aperture 96. A size ratio of the comer radius R relative to the aperture width W is used to configure the aperture 98 as previously described. In an embodiment, the size ratio is 0.22 wherein the corner radius R may be approximately 12 in. and the aperture width may be approximately 53.59 in.
Referring to Figs. 7A-7B, top and side views, respectively, of the transition piece 82 are shown. The transition piece 82 is located between a collector (i.e. between either collector 62, 94) and the exhaust stack 55 and provides an exhaust gas flow path from a collector 62, 94 to the exhaust stack 55. The transition piece 82 includes a transition wall 114 having lower 116 and upper 118 wall portions. The lower 116 and upper 118 wall portions include lower 120 and upper 122 apertures, respectively. In particular, the lower portion 116 includes first 124 and second 126 straight sections connected by associated end sections corresponding to the first 98 and second 100 end sections such that the shape of the lower aperture 120 corresponds to the shape of the collector aperture 96. Alternatively, the lower aperture 120 may have a shape corresponding to the collector aperture 80.
The shape of the upper aperture 122 corresponds to a shape of a stack aperture of the exhaust stack 55. In an embodiment, the upper aperture 122 may have a substantially round shape. Thus, the upper aperture 122 of the transition piece 82 is configured to accommodate the size and shape of a stack aperture of the exhaust stack 55 and the lower aperture 120 of the transition piece 82 is configured to accommodate the size and shape of either the collector 80 or the collector 96. This enables attachment of the transition piece 82 to either collector 62 or collector 94 and the exhaust stack 55 to provide a flow path for the exhaust gas 52 that extends from either collector 62 or collector 94 to the exhaust stack 55.
While particular embodiments of the present disclosure have been illustrated and described, it would be obvious to those skilled in the art that various other changes and modifications can be made without departing from the spirit and scope of the disclosure. It is therefore intended to cover in the appended claims all such changes and modifications that are within the scope of this disclosure.

Claims

CLAIMS What is claimed is:
1. An exhaust gas collector (62) for a turbine (26) that generates exhaust gas (52) that flows along a first axis (68), wherein the exhaust gas (52) is vented via an exhaust stack (55), comprising;
first (64) and second (66) side walls separated by a circumferential wall (70) to form a plenum (74) that receives the exhaust gas (52) from the turbine (26), wherein the first side wall (64) includes a first aperture (72) for receiving a portion of the turbine (26) and the second side wall (66) includes a second aperture (76) that provides a clearance for an output shaft (50) of the turbine (26); and
a collector aperture (80) formed in a top portion (78) of the collector (62), wherein the collector aperture (80) provides a flow path for the exhaust gas (52) from the plenum (74) to the exhaust stack (55) and wherein a shape of the collector aperture (80) is defined by first (86) and second (88) straight sections and first (90) and second (92) curved end sections wherein the first curved end section (90) is located between first ends (86A, 86B) of the first (86) and second (88) straight sections and the second curved section (92) is located between second ends (86B, 88B) of the first (86) and second (88) straight sections.
2. The collector (62) according to claim 1, wherein the collector aperture (80) is configured by determining a size ratio of a radius R of either the first (90) or second (92) curved section relative to a width W of the collector aperture (80) between the first (86) and second (88) straight sections.
3. The collector (62) according to claim 2, wherein the size ratio is selected to reduce stress concentration in the collector (62) while simultaneously providing suitable gas flow for the exhaust gas (52).
4. The collector (62) according to claim 3, wherein a range for the size ratio for reducing stress concentration and simultaneously providing suitable exhaust gas (52) flow is 0.1 to 0.41.
5. The collector (62) according to claim 1, further including a transition piece (82) located between the collector (62) and the exhaust stack (55) wherein the transition piece (82) includes a first transition aperture (120) having a configuration substantially similar to that of the collector aperture (80) and a second transition aperture (122) having a configuration substantially similar to that of a stack aperture of the exhaust stack (55) wherein the collector aperture (80) has a different configuration than the stack aperture.
6. The collector (62) according to claim 1, wherein the collector aperture (80) is oriented such that flow path for the exhaust gas (52) is oriented in a direction that is not orthogonal to the first axis (68).
7. An exhaust gas collector (94) for a turbine (26) that generates exhaust gas (52) that flows along a first axis (68), wherein the exhaust gas (52) is vented via an exhaust stack (55), comprising;
first (64) and second (66) side walls separated by a circumferential wall (70) to form a plenum (74) that receives the exhaust gas (52) from the turbine (26), wherein the first side wall (64) includes a first aperture (72) for receiving a portion of the turbine (26) and the second side wall (66) includes a second aperture (76) that provides a clearance for an output shaft (50) of the turbine (26); and
a collector aperture (96) formed in a top portion (78) of the collector (94), wherein the collector aperture (96) provides a flow path for the exhaust gas (52) from the plenum (74) to the exhaust stack (55) and wherein a shape of the collector aperture (96) is defined by first (86) and second (88) straight sections and first (98) and second (100) end sections wherein the first end section (98) is located between first ends (86A, 88A) of the first (86) and second (88) straight section and the second end section (100) is located between second ends (86B, 88B) of the first (86) and second (88) straight sections and wherein the first (98) and second (100) end sections each include a flat (102 or 108) located between curved sections (104, 106 or 110, 112) of a respective end section (98, 100).
8. The collector (94) according to claim 7, wherein the collector aperture (96) is configured by determining a size ratio of a radius R of either a curved section (104, 106, 110, 112) relative to a width W of the collector aperture (96) between the first (86) and second (88) straight sections.
9. The collector (94) according to claim 8, wherein the size ratio is selected to reduce stress concentration in the collector (94) while simultaneously providing suitable gas flow for the exhaust gas (52).
10. The collector (94) according to claim 9, wherein a range for the size ratio for reducing stress concentration and simultaneously providing suitable exhaust gas flow is 0.1 to 0.41.
11. The collector (94) according to claim 7, further including a transition piece (82) located between the collector (94) and the exhaust stack (55) wherein the transition piece (82) includes a first transition aperture (120) having a configuration substantially similar to that of the collector aperture (96) and a second transition aperture (122) having a configuration substantially similar to that of a stack aperture of the exhaust stack (55) wherein the collector aperture (96) has a different configuration than the stack aperture.
12. The collector (94) according to claim 7, wherein the collector aperture (96) is oriented such that flow path for the exhaust gas (52) is oriented in a direction that is not orthogonal to the first axis (68).
13. An exhaust gas collector (62) for a turbine (26) that generates exhaust gas (52) that flows along a first axis (68), wherein the exhaust gas (52) is vented via an exhaust stack (55), comprising;
first (64) and second (66) side walls separated by a circumferential wall (70) to form a plenum (74) that receives the exhaust gas (52) from the turbine (26), wherein the first side wall (64) includes a first aperture (72) for receiving a portion of the turbine (26) and the second side wall (66) includes a second aperture (76) that provides a clearance for an output shaft (50) of the turbine (26);
a collector aperture (80) formed in a top portion (78) of the collector (62), wherein the collector aperture (80) provides a flow path for the exhaust gas (52) from the plenum (74) to the exhaust stack (55) and wherein a shape of the collector aperture (80) is defined by first (86) and second (88) straight sections and first (90) and second (92) curved end sections wherein the first curved end section (90) is located between first ends (86A, 86B) of the first (86) and second (88) straight sections and the second curved section (92) is located between second ends (86B, 88B) of the first (86) and second (88) straight sections; and
a transition piece (82) located between the collector (62) and the exhaust stack (55) wherein the transition piece (82) includes a first transition aperture (120) having a configuration substantially similar to that of the collector aperture (80) and a second transition aperture (122) having a configuration substantially similar to that of a stack aperture of the exhaust stack (55) wherein the collector aperture (80) has a different configuration than the stack aperture.
14. The collector (62) according to claim 13, wherein the collector aperture (80) is configured by determining a size ratio of a radius R of either the first (90) or second (92) curved section relative to a width W of the collector aperture (80) between the first (86) and second (88) straight sections.
15. The collector (62) according to claim 14, wherein the size ratio is selected to reduce stress concentration in the collector (62) while simultaneously providing suitable gas flow for the exhaust gas (52).
16. The collector (62) according to claim 15, wherein a range for the size ratio for reducing stress concentration and simultaneously providing suitable exhaust gas flow is 0.1 to 0.41.
17. The collector (62) according to claim 13, wherein the collector aperture (80) is oriented such that flow path for the exhaust gas (52) is oriented in a direction that is not orthogonal to the first axis (68).
PCT/US2018/025979 2018-04-04 2018-04-04 Exhaust gas collector for a turbine WO2019194797A1 (en)

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PCT/US2018/025979 WO2019194797A1 (en) 2018-04-04 2018-04-04 Exhaust gas collector for a turbine

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2440343A (en) * 2006-07-25 2008-01-30 Siemens Ag Gas turbine exhaust arrangement
EP1992789A1 (en) * 2007-05-18 2008-11-19 ABB Turbo Systems AG Exhaust gas turbine casing comprising a support element
US20140047813A1 (en) * 2012-08-17 2014-02-20 Solar Turbines Incorporated Exhaust collector with radial and circumferential flow breaks
US20150075131A1 (en) * 2013-09-19 2015-03-19 Solar Turbines Incorporated Exhaust collector with curved side panel
WO2016177644A1 (en) * 2015-05-07 2016-11-10 Rolls-Royce Plc A gas turbine engine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2440343A (en) * 2006-07-25 2008-01-30 Siemens Ag Gas turbine exhaust arrangement
EP1992789A1 (en) * 2007-05-18 2008-11-19 ABB Turbo Systems AG Exhaust gas turbine casing comprising a support element
US20140047813A1 (en) * 2012-08-17 2014-02-20 Solar Turbines Incorporated Exhaust collector with radial and circumferential flow breaks
US20150075131A1 (en) * 2013-09-19 2015-03-19 Solar Turbines Incorporated Exhaust collector with curved side panel
WO2016177644A1 (en) * 2015-05-07 2016-11-10 Rolls-Royce Plc A gas turbine engine

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