WO2008012294A2 - A gas turbine arrangement - Google Patents

A gas turbine arrangement Download PDF

Info

Publication number
WO2008012294A2
WO2008012294A2 PCT/EP2007/057595 EP2007057595W WO2008012294A2 WO 2008012294 A2 WO2008012294 A2 WO 2008012294A2 EP 2007057595 W EP2007057595 W EP 2007057595W WO 2008012294 A2 WO2008012294 A2 WO 2008012294A2
Authority
WO
WIPO (PCT)
Prior art keywords
collector
combustion gases
diffuser
arrangement
gas turbine
Prior art date
Application number
PCT/EP2007/057595
Other languages
French (fr)
Other versions
WO2008012294A3 (en
Inventor
Paul Roach
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 DE602007007334T priority Critical patent/DE602007007334D1/en
Priority to CN200780028092.2A priority patent/CN101495715B/en
Priority to US12/309,150 priority patent/US20090246010A1/en
Priority to EP07787838A priority patent/EP2044296B1/en
Publication of WO2008012294A2 publication Critical patent/WO2008012294A2/en
Publication of WO2008012294A3 publication Critical patent/WO2008012294A3/en

Links

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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/023—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines the working-fluid being divided into several separate flows ; several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths
    • 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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/06—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines traversed by the working-fluid substantially radially
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the turbine blading rotates about a centre line of the gas turbine arrangement, and the partition device runs parallel to the centre line, and extends radially from the centre line.
  • Fig 11 illustrates possible extensions to a shroud rim of the arrangement of Fig 5;
  • Figs 12, 13 and 14 illustrate respectively combustion gas flow in three gas turbine arrangements;
  • Fig 12 illustrates combustion gas flow in the diffuser 5 and collector 7 of the known gas turbine arrangement of Figs 1 to 4. It is to be noted that strong vortices occur in the annular main part 9 of the collector 7, and mixing of the vortical flows 13a, 13b occurs in the neck exit 11 of the collector 7.

Abstract

A gas turbine arrangement comprising: a passage (1), annular in cross section, for conveying combustion gases; located in the passage (1), turbine blading (3) to be driven by the combustion gases; a diffuser (5), annular in form, for diffusing the combustion gases following their passage through the turbine blading (3); and a collector (7) for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part (9), and a neck exit (11), wherein the combustion gases collected by the collector (7) are conveyed around the annular main part (9) of the collector (7) in opposite senses so as to arrive at the neck exit (11) of the collector travelling in opposed directions, wherein the neck exit (11) of the collector (7) includes a partition device (13) whereby the opposed direction flows at the neck exit (11) are kept separate.

Description

A gas turbine arrangement
The present invention relates to a gas turbine arrangement.
More particularly the present invention relates to a gas turbine arrangement comprising: a passage, annular in cross section, for conveying combustion gases; located in the passage, turbine blading to be driven by the combustion gases; a diffuser, annular in form, for diffusing the combustion gases following their passage through the turbine blading; and a collector for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part, and, located at a position around the annular main part, a neck exit, in use of the gas turbine arrangement, combustion gases collected by the collector being conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions.
One known such gas turbine arrangement is shown in Figs 1 to 4 of the accompanying drawings . Fig l is a cut away perspective view of the arrangement, Fig 2 is a partial longitudinal cross section of the arrangement, Fig 3 is a schematic diagram illustrating the passage of combustion gases through the arrangement, and Fig 4 is a cross section on the line IV-IV in Fig 3.
Referring to Figs 1 to 4, the gas turbine arrangement comprises: a passage 1, annular in cross section, for conveying combustion gases; located in the passage 1, turbine blading 3 to be driven by the combustion gases; a diffuser 5, annular in form, for diffusing the combustion gases following their passage through the turbine blading 3; and a collector 7 for collecting the combustion gases diffused by the diffuser 5, the collector 7 comprising an annular main part 9, and, located at a position around the annular main part 9, a neck exit 11.
In use of the gas turbine arrangement, combustion gases travel along passage 1, drive turbine blading 3, are diffused by diffuser 5, and are collected by collector 7. The combustion gases on leaving the diffuser 5 form within the collector 7 first and second opposite sense vortical flows 13a, 13b, see Fig 4. These vortical flows 13a, 13b are formed by virtue of the combustion gas flow separating off the shroud rim 15 of the diffuser 5, and rolling up, see arrows 17 in Fig 3. The flow is then convected around the annular main part 9 of the collector 7, forming the first and second opposite sense vortical flows 13a, 13b. These flows 13a, 13b meet at the top neck exit 11 of the collector 7 travelling in opposed directions .
The separating of the combustion gas flow off the shroud rim 15, and the meeting of the vortical flows 13a, 13b in the neck exit 11, result in the production of significant entropy in the flow. This is detrimental to the efficiency of the gas turbine arrangement .
According to the present invention there is provided a gas turbine arrangement comprising: a passage, annular in cross section, for conveying combustion gases; located in the passage, turbine blading to be driven by the combustion gases; a diffuser, annular in form, for diffusing the combustion gases following their passage through the turbine blading; and a collector for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part, and, located at a position around the annular main part, a neck exit, in use of the gas turbine arrangement, combustion gases collected by the collector being conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions, wherein the neck exit of the collector includes a partition device whereby the opposed direction flows at the neck exit are kept substantially separate .
In an arrangement according to the preceding paragraph, it is preferable that the turbine blading rotates about a centre line of the gas turbine arrangement, and the partition device runs parallel to the centre line, and extends radially from the centre line.
In an arrangement according to the preceding paragraph, it is preferable that the diffuser has a mouth whereby combustion gases leave the diffuser and enter the collector, the partition device comprises a first portion that extends over the mouth and a second portion that extends to one side of the mouth, and the second portion extends radially inward to a position closer to the centre line than the mouth.
In an arrangement according to the preceding paragraph, it is preferable that the side of the first portion that faces radially inwardly increases in distance from the centre line as the distance from the second portion increases.
In an arrangement according to any one of the preceding four paragraphs, it is preferable that the partition device comprises a flat plate. In an arrangement according to any one of the preceding five paragraphs, it is preferable that the diffuser has a curved shroud rim whereat combustion gases leave the diffuser and enter the collector, the shroud rim has an extension operative to increase pressure recovery in the gas turbine arrangement, and the extension comprises a flat rim extension that is generally planar in form and forms a discontinuity with the curved shroud rim.
In an arrangement according to any one of the preceding five paragraphs but one, it is preferable that the diffuser has a curved shroud rim whereat combustion gases leave the diffuser and enter the collector, the shroud rim has an extension operative to increase pressure recovery in the gas turbine arrangement, and the extension comprises a spiral rim extension that continues or extends the curve of the curved shroud rim so as to form a spiral.
The invention will now be described, by way of example, with reference to the accompanying drawings, in which:
Fig 1, already referred to, is a cut away perspective view of a known gas turbine arrangement;
Fig 2, also already referred to, is a partial longitudinal cross section of the arrangement of Fig 1; Fig 3, also already referred to, is a schematic diagram illustrating the passage of combustion gases through the arrangement of Fig 1;
Fig 4, also already referred to, is a cross section on the line IV-IV in Fig 3; Fig 5 is a cut away perspective view of a gas turbine arrangement in accordance with the present invention;
Fig 6 is a partial longitudinal cross section of the arrangement of Fig 5; Fig 7 is a schematic diagram illustrating the passage of combustion gases through the arrangement of Fig 5;
Fig 8 is a cross section on the line VIII-VIII in Fig 7;
Fig 9 illustrates in greater detail the form and location of a splitter plate of the arrangement of Fig 5;
Fig 10 illustrates alternative splitter plates to the splitter plate of Fig 9;
Fig 11 illustrates possible extensions to a shroud rim of the arrangement of Fig 5; Figs 12, 13 and 14 illustrate respectively combustion gas flow in three gas turbine arrangements;
Figs 15, 16 and 17 are plan views corresponding respectively to Figs 12, 13 and 14;
Figs 18, 19 and 20 are side views corresponding respectively to Figs 12, 13 and 14;
Figs 21 and 22 are perspective views corresponding respectively to Figs 13 and 14; and
Fig 23 illustrates an alternative form of partition device to the flat plates of earlier Figs.
In Figs 5 to 23, the same elements as appearing in Figs 1 to
4 are labelled with the same reference numerals.
Referring to Figs 5 to 8, the arrangement of Figs 5 to 8 is the same as that of Figs 1 to 4 with the exception that the neck exit 11 of the collector 7 includes a partition device in the form of a splitter plate 19 whereby the opposed direction vortical flows 13a, 13b at the neck exit 11 are kept substantially separate, i.e. the splitter plate 19 isolates the vortical flows 13a, 13b one from the other. The splitter plate 19 runs parallel to the centre line A of the gas turbine arrangement, and extends radially from the centre line A. Preventing meeting of the vortical flows 13a, 13b, reduces entropy production in the flow of combustion gases through the gas turbine arrangement, consequently improving the efficiency of the arrangement. The splitter plate 19 has the advantage that it is simple in design, and can be retrofitted to current gas turbine arrangement collectors .
Fig 9 illustrates the precise shape and location of the splitter plate 19 in the arrangement of Figs 5 to 8. The diffuser 5 has a mouth 35 whereby combustion gases leave the diffuser 5 and enter the collector 7. The splitter plate 19 comprises a first portion 37 that extends over the mouth 35 and a second portion 39 that extends to one side of the mouth 35. It can be seen from Fig 9 that the second portion 39 extends radially inward to a position 41 closer to the centre line A than the mouth 35. It can also be seen from Fig 9 that the side 43 of the first portion 37 that faces radially inwardly progressively increases in distance from the centre line A as the distance from the second portion 39 increases.
Fig 10 illustrates the precise shape of three alternative splitter plates 21, 23, 25. Plate 21 is the same as plate 19 except that the side 45 of plate 21 corresponding to side 43 of plate 19 remains at a constant distance from the centre line A. Plate 23 may be derived from plate 21 by removing that portion of plate 21 which is radially nearer to the centre line A than side 45 of plate 21. Plate 25 may be derived from plate 23 by removing a further radially inner portion of plate 23. It is to be noted that in the case of both plates 23, 25, the sides 47 of the plates 23, 25 that face radially inwardly remain at a constant distance from the centre line A. It is also to be noted that the sides 47 are radially further from the centre line A than the mouth 35 of the diffuser 5.
Fig 11 illustrates two possible extensions 29, 31 to the shroud rim 15 of the diffuser 5 of the arrangement of Figs 5 to 8. The extensions 29, 31 operate to increase the pressure recovery in the gas turbine arrangement, over and above that obtained using a splitter plate alone. The extensions 29, 31 diffuse the combustion gas flow in a more controlled manner, weakening the vortices formed in the collector 7. Extension 29 comprises a flat rim extension, and is generally planar in form, and forms a discontinuity with the shroud rim 15. Extension 31 comprises a spiral rim extension, and continues or extends the curve of the shroud rim 15 so as to form a spiral.
Fig 12 illustrates combustion gas flow in the diffuser 5 and collector 7 of the known gas turbine arrangement of Figs 1 to 4. It is to be noted that strong vortices occur in the annular main part 9 of the collector 7, and mixing of the vortical flows 13a, 13b occurs in the neck exit 11 of the collector 7.
Fig 13 illustrates combustion gas flow in the diffuser 5 and collector 7 of a gas turbine arrangement including a splitter plate 19 only, i.e. not including an extension 29, 31 to the shroud rim 15 as shown in Fig 11. It is to be noted that strong vortices still occur in the annular main part 9 of the collector 7, but no mixing of the vortical flows 13a, 13b occurs in the neck exit 11 of the collector 7.
Fig 14 illustrates combustion gas flow in the diffuser 5 and collector 7 of a gas turbine arrangement including a splitter plate 19 and a flat rim extension 29. It is to be noted that only weak vortices occur in the annular main part 9 of the collector 7, and, in addition, no mixing of the vortical flows 13a, 13b occurs in the neck exit 11 of the collector 7.
Figs 15, 16 and 17 are views taken from above in Figs 12, 13 and 14 respectively. Splitter plate 19 is to be noted in Figs 16 and 17. Flat rim extension 29 is to be noted in Fig 17.
Figs 18, 19 and 20 are views taken from the left side in Figs 12, 13 and 14 respectively. Splitter plate 19 is to be noted in Figs 19 and 20. Flat rim extension 29 is to be noted in Fig 20.
Figs 21 and 22 are perspective views corresponding respectively to Figs 13 and 14. Splitter plate 19 is to be noted in Figs 21 and 22. Flat rim extension 29 is to be noted in Fig 22.
In the above description, the partition device in the neck exit 11 of the collector 7 takes the form of a flat plate. It is to be realised that the partition device could take other forms that achieve the required separation of the opposed direction vortical flows 13a, 13b in the neck exit 11. Fig 23 shows an example of an alternative partition device 33, comprising an upper flat plate part 51 and a lower substantially triangular cross section part 53 having concave sides. It is to be noted that the cross section shown in Fig 23 corresponds to second portion 39 in Fig 9, and that the first portion 37 in Fig 9 remains as it is, i.e. a flat plate. The upper and lower parts 51, 53 of the partition device 33 meet at a height corresponding to the height of the obtuse angle 55 in Fig 9.

Claims

Claims :
1. A gas turbine arrangement comprising: a passage, annular in cross section, for conveying combustion gases; located in the passage, turbine blading to be driven by the combustion gases; a diffuser, annular in form, for diffusing the combustion gases following their passage through the turbine blading; and a collector for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part, and, located at a position around the annular main part, a neck exit, in use of the gas turbine arrangement, combustion gases collected by the collector being conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions, wherein the neck exit of the collector includes a partition device whereby the opposed direction flows at the neck exit are kept substantially separate .
2. An arrangement according to claim 1, wherein the turbine blading rotates about a centre line of the gas turbine arrangement, and the partition device runs parallel to the centre line, and extends radially from the centre line.
3. An arrangement according to claim 2, wherein the diffuser has a mouth whereby combustion gases leave the diffuser and enter the collector, the partition device comprises a first portion that extends over the mouth and a second portion that extends to one side of the mouth, and the second portion extends radially inward to a position closer to the centre line than the mouth.
4. An arrangement according to claim 3, wherein the side of the first portion that faces radially inwardly increases in distance from the centre line as the distance from the second portion increases.
5. An arrangement according to any one of the preceding claims wherein the partition device comprises a flat plate.
6. An arrangement according to any one of the preceding claims, wherein the diffuser has a curved shroud rim whereat combustion gases leave the diffuser and enter the collector, the shroud rim has an extension operative to increase pressure recovery in the gas turbine arrangement, and the extension comprises a flat rim extension that is generally planar in form and forms a discontinuity with the curved shroud rim.
7. An arrangement according to any one of claims 1 to 5, wherein the diffuser has a curved shroud rim whereat combustion gases leave the diffuser and enter the collector, the shroud rim has an extension operative to increase pressure recovery in the gas turbine arrangement, and the extension comprises a spiral rim extension that continues or extends the curve of the curved shroud rim so as to form a spiral.
PCT/EP2007/057595 2006-07-25 2007-07-24 A gas turbine arrangement WO2008012294A2 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE602007007334T DE602007007334D1 (en) 2006-07-25 2007-07-24 GAS TURBINE ARRANGEMENT
CN200780028092.2A CN101495715B (en) 2006-07-25 2007-07-24 Gas turbine exhaust arrangement
US12/309,150 US20090246010A1 (en) 2006-07-25 2007-07-24 Gas turbine arrangement
EP07787838A EP2044296B1 (en) 2006-07-25 2007-07-24 A gas turbine arrangement

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0614687.2 2006-07-25
GB0614687A GB2440343B (en) 2006-07-25 2006-07-25 A gas turbine arrangement

Publications (2)

Publication Number Publication Date
WO2008012294A2 true WO2008012294A2 (en) 2008-01-31
WO2008012294A3 WO2008012294A3 (en) 2008-03-13

Family

ID=36998632

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2007/057595 WO2008012294A2 (en) 2006-07-25 2007-07-24 A gas turbine arrangement

Country Status (8)

Country Link
US (1) US20090246010A1 (en)
EP (1) EP2044296B1 (en)
CN (1) CN101495715B (en)
DE (1) DE602007007334D1 (en)
ES (1) ES2346159T3 (en)
GB (1) GB2440343B (en)
RU (1) RU2441987C2 (en)
WO (1) WO2008012294A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008142044A2 (en) * 2007-05-18 2008-11-27 Abb Turbo Systems Ag Turbine housing

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0800451D0 (en) 2008-01-11 2008-02-20 Cummins Turbo Tech Ltd A turbomachine system and turbine therefor
US8109720B2 (en) * 2009-03-31 2012-02-07 General Electric Company Exhaust plenum for a turbine engine
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser
US8398359B2 (en) * 2010-02-17 2013-03-19 General Electric Company Exhaust diffuser
US8276390B2 (en) 2010-04-15 2012-10-02 General Electric Company Method and system for providing a splitter to improve the recovery of compressor discharge casing
US8757969B2 (en) * 2010-09-15 2014-06-24 General Electric Company Turbine exhaust plenum
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
CN102434225B (en) * 2011-10-18 2014-12-03 中国南方航空工业(集团)有限公司 Sealing structure of booster impeller shaft
US20140026999A1 (en) * 2012-07-25 2014-01-30 Solar Turbines Incorporated Exhaust diffuser for a gas turbine engine having curved and offset struts
US20140047813A1 (en) * 2012-08-17 2014-02-20 Solar Turbines Incorporated Exhaust collector with radial and circumferential flow breaks
US20140119910A1 (en) * 2012-10-29 2014-05-01 General Electric Company Turbine exhaust hood and related method
DE102013001231B4 (en) * 2013-01-25 2014-10-09 Voith Patent Gmbh Exhaust gas routing of an exhaust gas turbine for a turbocompound system and turbocompound system
US9644496B2 (en) * 2013-03-13 2017-05-09 General Electric Company Radial diffuser exhaust system
FR3009026B1 (en) * 2013-07-24 2018-01-05 Safran Aircraft Engines CENTRAL EXHAUST BODY FOR A TURBOMACHINE
US9476324B2 (en) 2013-09-19 2016-10-25 Solar Turbines Incorporated Exhaust collector with curved side panel
US20150240667A1 (en) * 2014-02-26 2015-08-27 General Electric Company Exhaust plenum for radial diffuser
WO2015156804A1 (en) * 2014-04-10 2015-10-15 Siemens Aktiengesellschaft Gas turbine exhaust system
FR3030633B1 (en) * 2014-12-22 2019-04-12 Airbus Helicopters EXHAUST PIPE OF A TURBOMOTEUR WHOSE OUTLET IS PERPENDICULAR TO THE AXIS OF ROTATION OF THE TURBOMOTEUR
BR112017021584B1 (en) * 2015-04-24 2023-01-17 Nuovo Pignone Tecnologie Srl GAS TURBINE ENGINE
DE102017124467A1 (en) * 2017-10-19 2019-04-25 Abb Turbo Systems Ag Diffuser arrangement of an exhaust gas turbine
WO2019194797A1 (en) * 2018-04-04 2019-10-10 Siemens Aktiengesellschaft Exhaust gas collector for a turbine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3120374A (en) * 1962-08-03 1964-02-04 Gen Electric Exhaust scroll for turbomachine
JPS5464204A (en) * 1977-10-31 1979-05-23 Hitachi Ltd Low pressure casing of turbine
FR2469563A1 (en) * 1979-11-14 1981-05-22 Nissan Motor GAS TURBINE ENGINE WITH DIFFUSER ARRANGEMENT AND EXHAUST GAS COLLECTOR
US5257906A (en) * 1992-06-30 1993-11-02 Westinghouse Electric Corp. Exhaust system for a turbomachine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191402848A (en) * 1914-02-03 1914-12-24 Karl Baumann Improvements in Steam Turbines.
US2840342A (en) * 1953-03-17 1958-06-24 David H Silvern Turbine exhaust
US2796732A (en) * 1953-05-12 1957-06-25 Napier & Son Ltd Gas producing apparatus of the gas turbine type
GB786088A (en) * 1955-03-30 1957-11-13 Napier & Son Ltd Exhaust duct assemblies for aircraft propulsion units of the combustion turbine type
US3802187A (en) * 1972-06-01 1974-04-09 Avco Corp Exhaust system for rear drive engine
US3995432A (en) * 1975-07-28 1976-12-07 United Technologies Corporation Collector
SU857516A1 (en) * 1978-11-27 1981-08-23 Харьковский Ордена Ленина Политехнический Институт Им. В.И.Ленина Axial turbine outlet pipe
AT383396B (en) * 1984-08-17 1987-06-25 Proizv Ob Turbostroenia LOW PRESSURE CYLINDERS OF A STEAM TURBINE
US5188510A (en) * 1990-11-21 1993-02-23 Thomas R. Norris Method and apparatus for enhancing gas turbo machinery flow
US5174120A (en) * 1991-03-08 1992-12-29 Westinghouse Electric Corp. Turbine exhaust arrangement for improved efficiency
US6419448B1 (en) * 2000-03-20 2002-07-16 Jerzy A. Owczarek Flow by-pass system for use in steam turbine exhaust hoods
US20050042087A1 (en) * 2003-05-28 2005-02-24 Hamer Andrew J. Method and apparatus for reducing total pressure loss in a turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3120374A (en) * 1962-08-03 1964-02-04 Gen Electric Exhaust scroll for turbomachine
JPS5464204A (en) * 1977-10-31 1979-05-23 Hitachi Ltd Low pressure casing of turbine
FR2469563A1 (en) * 1979-11-14 1981-05-22 Nissan Motor GAS TURBINE ENGINE WITH DIFFUSER ARRANGEMENT AND EXHAUST GAS COLLECTOR
US5257906A (en) * 1992-06-30 1993-11-02 Westinghouse Electric Corp. Exhaust system for a turbomachine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008142044A2 (en) * 2007-05-18 2008-11-27 Abb Turbo Systems Ag Turbine housing
WO2008142044A3 (en) * 2007-05-18 2009-11-19 Abb Turbo Systems Ag Gas outlet housing of an exhaust turbine with a support element

Also Published As

Publication number Publication date
GB2440343B (en) 2008-08-13
RU2009106437A (en) 2010-08-27
RU2441987C2 (en) 2012-02-10
EP2044296A2 (en) 2009-04-08
CN101495715B (en) 2012-06-20
EP2044296B1 (en) 2010-06-23
CN101495715A (en) 2009-07-29
WO2008012294A3 (en) 2008-03-13
US20090246010A1 (en) 2009-10-01
ES2346159T3 (en) 2010-10-11
GB2440343A (en) 2008-01-30
GB0614687D0 (en) 2006-08-30
DE602007007334D1 (en) 2010-08-05

Similar Documents

Publication Publication Date Title
EP2044296B1 (en) A gas turbine arrangement
CA2557493C (en) Blade or vane for a turbomachine
US10415392B2 (en) End wall configuration for gas turbine engine
CN1333153C (en) Impeller for radial turbine
US8092178B2 (en) Turbine blade for a gas turbine engine
US20070116571A1 (en) Rotor assembly with cooling air deflectors and method
US8398359B2 (en) Exhaust diffuser
US20140212260A1 (en) Airfoil Assembly with Paired Endwall Contouring
US8851833B2 (en) Blades
CN101148994A (en) Dust hole dome blade
CN104040256A (en) Separation device comprising a swirler
EP1726782A3 (en) Turbine blade trailing edge construction
US20130051974A1 (en) Gas turbine engines and methods for cooling components thereof with mid-impeller bleed cooling air
CN101135318A (en) Blade wheel structure and centrifugal fan device using the same
RU2013128549A (en) TURBO MACHINE SHOVEL
CN103202680A (en) Dust separation device for improving separation efficiency of dust collector
US20100254809A1 (en) Steam turbine stage
CN203670007U (en) Transition pipe provided with airfoil profile pieces and hot gas path assembly used for turbine
US8790084B2 (en) Airfoil and method of fabricating the same
US20140133957A1 (en) Method of diffusing a gas turbine compression stage, and diffusion stage for implementing same
CA2776536A1 (en) Blade for a gas turbine engine
JP2002349201A (en) Turbin rotor blade
CN102667176A (en) Centrifugal pump
JPS6327097Y2 (en)
CN113906222A (en) Stator blade for a centrifugal compressor

Legal Events

Date Code Title Description
WWE Wipo information: entry into national phase

Ref document number: 200780028092.2

Country of ref document: CN

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 07787838

Country of ref document: EP

Kind code of ref document: A2

WWE Wipo information: entry into national phase

Ref document number: 2007787838

Country of ref document: EP

WWE Wipo information: entry into national phase

Ref document number: 1/DELNP/2009

Country of ref document: IN

WWE Wipo information: entry into national phase

Ref document number: 12309150

Country of ref document: US

NENP Non-entry into the national phase

Ref country code: DE

ENP Entry into the national phase

Ref document number: 2009106437

Country of ref document: RU

Kind code of ref document: A