EP2412941A1 - Diffuseur d'échappement pour une turbine à gaz et procédé correspondant - Google Patents

Diffuseur d'échappement pour une turbine à gaz et procédé correspondant Download PDF

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Publication number
EP2412941A1
EP2412941A1 EP10007757A EP10007757A EP2412941A1 EP 2412941 A1 EP2412941 A1 EP 2412941A1 EP 10007757 A EP10007757 A EP 10007757A EP 10007757 A EP10007757 A EP 10007757A EP 2412941 A1 EP2412941 A1 EP 2412941A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
gas
flow
diffuser wall
wall
Prior art date
Legal status (The legal status 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 status listed.)
Withdrawn
Application number
EP10007757A
Other languages
German (de)
English (en)
Inventor
Alexander R. Beeck
Bonnie D. Marini
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to EP10007757A priority Critical patent/EP2412941A1/fr
Priority to EP11740594.4A priority patent/EP2598725B1/fr
Priority to JP2013521061A priority patent/JP5551316B2/ja
Priority to US13/811,943 priority patent/US20130121806A1/en
Priority to PCT/EP2011/062246 priority patent/WO2012013529A1/fr
Priority to CN201180036687.9A priority patent/CN103026009B/zh
Publication of EP2412941A1 publication Critical patent/EP2412941A1/fr
Withdrawn legal-status Critical Current

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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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure

Definitions

  • the present invention relates to exhaust diffusers for gas turbines, particularly for gas turbines in stationary or land based applications.
  • exhaust diffusers serve to reduce the speed of the exhaust flow in a gas turbine and to thus recover pressure from the exhaust gas coming from the last stage of the turbine.
  • the reduction in gas speed reduces the stress associated with the fluid flow on the exhaust equipment and enhances the performance levels of the turbine by recovering pressure from the exhaust gas, thus limiting head loss of the flow.
  • the pressure recovery from the exhaust gas is directly proportional to the outlet to inlet area ratio of the diffuser, which controls amount of effective flow diffusion following the last turbine stage.
  • a high outlet to inlet area ratio for a given axial length of the diffuser i.e., large diffuser angle
  • causes rapid expansion of the gas leading to a separation of flow of the gas from the diffuser wall which, in turn, causes a reduction in the pressure recovery by the diffuser.
  • Past attempts to solve the issue of flow separation from the diffuser wall involve the use of boundary layer control, for example, by suction or blowing, turbulators, among others.
  • exhaust diffusers are designed to have area ratios that provide a maximum pressure recovery at full load, taking into account the flow separation at full load. In such a case, the pressure recovery, and hence the work extracted by the turbine, is substantially reduced when the gas turbine operates at part-load.
  • the object of the present invention is to provide an exhaust diffuser assembly for a stationary gas turbine, and a method thereof, for achieving higher pressure recovery at different operating loads by reducing or eliminating excessive flow separation.
  • the underlying idea of the present invention is to provide a mechanism of controlling pressure recovery in an exhaust diffuser by controlling the geometry of the diffuser.
  • the proposed exhaust diffuser assembly has a variable geometry diffuser wall, which allows the divergence angle of the diffuser wall with respect to the longitudinal diffuser axis to be adjusted, so as to cause a resultant flow field of the gas that is attached to the diffuser wall.
  • the variability of diffuser wall geometry allows adaptability of the proposed diffuser assembly for adjustments in mass flows, i.e., operating loads.
  • said diffuser geometry control means comprises one or more actuators disposed on a surface said diffuser wall, said one or more actuators being adapted to exert an adjustable pressure said diffuser wall to resultantly adjust said divergence angle ' ⁇ ' of said diffuser wall.
  • said one or more actuators are controllable for increasing said divergence angle ' ⁇ ' to cause a resultant flow field beyond a point of flow separation of said gas from said diffuser wall and subsequently reducing said divergence angle ' ⁇ ' to re-attach the flow of said gas to said diffuser wall, so as to cause a resultant flow of said gas through said diffuser wall that is substantially proximate and prior to said point of flow separation. Since pressure recovery increases with increase in the rate of expansion (i.e., divergence angle) for attached flow, maintaining the flow field just before separation point for any given mass-flow rate would maximize the pressure recovery at that mass -flow rate
  • the proposed diffuser assembly further comprises a pressure probe disposed in a flow path of said gas through flowing said diffuser wall, wherein said point of flow separation is detected based on a decrease in sensed pressure between two progressively increasing settings of the divergence angle ' ⁇ '.
  • the proposed diffuser assembly further comprises a sonic probe disposed in a flow path of said gas inside said diffuser wall to detect said point of flow separation.
  • said point of flow separation is determined by flow visualization means adapted for detecting local direction of flow.
  • said diffuser wall is made of a piece of sheet metal wound to spiral form. Such a diffuser wall provides increased elasticity for adjustment of divergence angle.
  • said diffuser wall is made from a piece of sheet metal wound into a conical shape, wherein the edges of said piece of sheet metal are slidable against each other.
  • said diffuser wall comprises an adjustable portion having a rectangular cross-section, wherein the diffuser wall at said adjustable portion is flexible attached to a fixed portion by a hinge.
  • said diffuser wall has a rectangular cross-sectional geometry formed by angular plates forming corners of the rectangle, said angular plates being interspaced by and flat plates over which said angular plates are slidable such that said rectangular cross-sectional shape is adjustable along diagonal directions.
  • This allows the rectangular geometry of the diffuser wall to be uniformly varied (maintaining the same aspect ratio) along the direction of the diagonals of the rectangle by placing actuators at the corner of the rectangle.
  • an exhaust diffuser assembly 1 (also referred to as "diffuser 1") for a stationary gas turbine, for example, used in power generation and mechanical drives in land based applications.
  • the diffuser 1 has an inlet 3 having a first cross-sectional area A 1 for receiving a mainflow gas from a last stage of a turbine section 60.
  • the gas 5 flows along a longitudinal axis 2 through a conduit defined by a diverging diffuser wall 7 extending from the diffuser inlet 3 to a diffuser outlet 4 having a second cross-sectional area A 2 .
  • the diffuser outlet 4 directs the gas 5 to an exhaust duct 80.
  • the diffuser wall 7 serves to recover pressure from the gas by expanding the gas between the inlet 3 and the outlet 4. This reduces the total head loss of the gas, thereby increasing the work extracted from the gas 5.
  • the diffuser wall 7 makes an angle of divergence ' ⁇ ' with respect to the longitudinal axis 2. In conventional diffusers, the divergence angle is normally fixed at about 5-6°.
  • the area ratio 'R' increases with increase in divergence angle ' ⁇ '.
  • the pressure recovery increases with increase in divergence angle ' ⁇ ' or area ratio R, till the flow of the gas 5 is separated from the diffuser wall 7. Separation of flow reduces the pressure recovery from the gas 5.
  • the divergence angle ' ⁇ ' is adjusted to cause a resultant flow of the gas 5 that is attached to the diffuser wall 7.
  • the diffuser wall 7 has an adjustable geometry wherein the angle ' ⁇ ' may be varied. Exemplary embodiments of an adjustable geometry diffuser wall are discussed below referring to FIGS 3-7 .
  • variable seals 12 are provided at the connection of the diffuser wall 7 to the exhaust duct 80.
  • one or more actuators 9 are disposed on a surface (inner or outer) of the diffuser wall 7.
  • the actuators 9 are disposed on the outer surface of the diffuser wall 7.
  • the actuators 9 may comprise, for example, hydraulically or pneumatically operated actuators that are controlled by a controller 10 to exert an adjustable pressure on the diffuser wall 7 to resultantly adjust the divergence angle ' ⁇ ' of the diffuser wall 7.
  • the pressure recovery increases with increase in divergence angle ' ⁇ ' or area ratio 'R'.
  • the pressure recovery is maximized by maintaining a flow field of the gas 5 within the diffuser wall 7 that is just before the point of flow separation.
  • the actuators 9 are controlled to first increase the divergence angle ' ⁇ ' or area ratio 'R' to cause a resultant flow field beyond a point of flow separation. Subsequently, the actuators 9 are controlled to reduce the divergence angle ' ⁇ ' or area ratio 'R' to re-attach the flow to the diffuser wall 7 and to cause a resultant flow field that is prior to and proximate to the point of flow separation.
  • the point of flow separation is detected by a flow sensor 11 disposed in the flow path of the gas 5 inside the diffuser wall 7.
  • the flow sensor 7 may include, for example, a pressure probe.
  • the sensed pressure values by the pressure probe 11 increases. This is illustrated by a curve 13 in FIG 2 , wherein the axis 14 represents angle of divergence ' ⁇ ' and the axis 15 represents the corresponding sensed pressure 'P' by the pressure probe 11 disposed in the flow path of the gas 5.
  • the proposed technique in this embodiment involves increasing ' ⁇ ' to cause a flow field beyond the point 16 of flow separation, to identify the threshold angle ⁇ S , and to then reduce ' ⁇ ' to a value ⁇ D less than ⁇ S so as to re-attach the flow to the diffuser wall and to cause the resultant flow field to reach a point 17 that is just before the point 16 of flow separation.
  • a portion of the curve 13 in the region of the separation point 16 is flat having a slope equal or nearly equal to zero.
  • the flow field corresponding to this portion is preferably avoided as this indicates is an unstable flow field where separated and attached flow alternate.
  • the desired point 17 that is "substantially proximate and prior to" the point 16 of flow separation is determined, in this case, as the closest point to the point 16 on the curve 13 that has a positive slope.
  • the flow sensor 11 to detect the point of flow separation may comprise a sonic probe. Still alternately, the point of flow separation may be detected using flow visualization or imaging techniques which detect the local direction of flow.
  • the adjustable geometry which enables the forcing of the flow beyond the point of flow separation point allows the identification of the point of flow separation. Once the point of flow separation is identified, the geometry of the diffuser may be adjusted to re-attach the flow to the diffuser wall.
  • the adjustable geometry proposed herein allows for adaptability of the technique discussed above to changes in mass-flow, such that the pressure recovery may be maximized even when the gas turbine is operating at part load.
  • the diffuser wall 7 is made of a sheet 18 of metal wound in several turns in a spiral form to form conical shape.
  • the spiral form provides the required elasticity for geometric adjustments.
  • Actuators 9 may be disposed on the outer surface of one or more of these turns to, which, when actuated, apply the required pressure to increase or decrease the divergence angle of the diffuser wall 7.
  • the diffuser wall 7 may be made from a sheet 20 of metal wound in a conical shape, such that the ends 21 and 22 are not welded to each other, but slide against each other on the application of pressure by one or more actuators 9 disposed on the outer surface of the diffuser wall 7, such that divergence angle or area ratio may be varied.
  • the diffuser wall 7 is made of sheet metal and includes an adjustable portion 23 having a rectangular cross-section and a fixed portion 24, which may have a circular cross-section at the inlet 3.
  • the rectangular portion 23 is made of flat plates 25, 26, 27, 28, one or more of which are flexibly connected to the fixed portion 24 by means of hinges 29, that allow the respective side 25, 26, 27, 28 to swivel with respect to the fixed portion 24 on application of pressure from the actuator 9 disposed thereon, to thus adjust the divergence angle/area ratio.
  • the plates 25 and 27 are hinged such that the direction of angular movement is as illustrated by the arrows 30.
  • the diffuser wall 7 has a rectangular cross-section formed by flat plates 31, 32, 33, 34 that are directly connected to a circular turbine manifold 35 by flexible joints 36 so as to allow angular movements of opposite plates 31 and 33 as depicted by the arrow 37.
  • the diffuser wall 7 is made of angular plates 38, 39, 40, 41 that define the corners of a rectangle (herein, square).
  • the angular plates 38, 39, 40, 41 are interspaced by flat plates 42, 43, 44, 45, which, together with the angular plates 38, 39, 40, 41 form the sides of the rectangular diffuser wall 7. As illustrated, the angular plates are slidable against the flat plates 42, 43, 44, 45 such that the rectangular cross-sectional geometry of the diffuser wall 7 may be adjusted along diagonal directions 46 and 47 by actuators (not shown) disposed on the corners 48, 49, 50, 51 of the rectangular diffuser wall 7.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10007757A 2010-07-26 2010-07-26 Diffuseur d'échappement pour une turbine à gaz et procédé correspondant Withdrawn EP2412941A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP10007757A EP2412941A1 (fr) 2010-07-26 2010-07-26 Diffuseur d'échappement pour une turbine à gaz et procédé correspondant
EP11740594.4A EP2598725B1 (fr) 2010-07-26 2011-07-18 Diffuseur d'échappement pour turbine à gaz et procédé d'utilisation de ce diffuseur
JP2013521061A JP5551316B2 (ja) 2010-07-26 2011-07-18 ガスタービン用の排気ディフューザーおよびその方法
US13/811,943 US20130121806A1 (en) 2010-07-26 2011-07-18 Exhaust diffuser for a gas turbine, and method thereof
PCT/EP2011/062246 WO2012013529A1 (fr) 2010-07-26 2011-07-18 Diffuseur d'échappement pour turbine à gaz et procédé d'utilisation de ce diffuseur
CN201180036687.9A CN103026009B (zh) 2010-07-26 2011-07-18 用于燃气轮机的排气扩压器及其方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10007757A EP2412941A1 (fr) 2010-07-26 2010-07-26 Diffuseur d'échappement pour une turbine à gaz et procédé correspondant

Publications (1)

Publication Number Publication Date
EP2412941A1 true EP2412941A1 (fr) 2012-02-01

Family

ID=43242599

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10007757A Withdrawn EP2412941A1 (fr) 2010-07-26 2010-07-26 Diffuseur d'échappement pour une turbine à gaz et procédé correspondant
EP11740594.4A Not-in-force EP2598725B1 (fr) 2010-07-26 2011-07-18 Diffuseur d'échappement pour turbine à gaz et procédé d'utilisation de ce diffuseur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11740594.4A Not-in-force EP2598725B1 (fr) 2010-07-26 2011-07-18 Diffuseur d'échappement pour turbine à gaz et procédé d'utilisation de ce diffuseur

Country Status (5)

Country Link
US (1) US20130121806A1 (fr)
EP (2) EP2412941A1 (fr)
JP (1) JP5551316B2 (fr)
CN (1) CN103026009B (fr)
WO (1) WO2012013529A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2489738B (en) * 2011-04-08 2013-07-03 Rolls Royce Plc Improvements in or relating to gas turbine engine transition ducts
GB2506876A (en) * 2012-10-10 2014-04-16 Rolls Royce Plc A gas turbine engine system transition duct
US10329945B2 (en) * 2015-04-21 2019-06-25 Siemens Energy, Inc. High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry
CN105937415B (zh) * 2016-06-08 2017-06-06 西安交通大学 一种可适应大范围背压及流量的超临界二氧化碳透平装置
CN116940747A (zh) * 2021-03-24 2023-10-24 三菱重工业株式会社 涡轮及燃气涡轮

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4398865A (en) * 1978-11-10 1983-08-16 Garkusha Anatoly V Exhaust pipe of turbine
US20080063516A1 (en) * 2006-09-08 2008-03-13 Siemens Power Generation, Inc. Adjustable turbine exhaust flow guide and bearing cone assemblies
US20090068006A1 (en) * 2007-05-17 2009-03-12 Elliott Company Tilted Cone Diffuser for Use with an Exhaust System of a Turbine

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB607686A (en) * 1945-02-01 1948-09-03 Power Jets Res & Dev Ltd Improvements relating to duct inlets for use in supersonic conditions
US3391869A (en) * 1966-05-23 1968-07-09 Rohr Corp Variable cone area convergentdivergent nozzle system
FR2537657A1 (fr) * 1982-12-08 1984-06-15 Snecma Tuyere a section variable pour un turboreacteur et avion comportant un tel equipement
DE19905994A1 (de) * 1999-02-15 2000-08-24 Peter Kraus Vorrichtung und Verfahren zur Aufhebung von Stoß-Grenzschicht-Oszillationen bei kreisringförmigen Diffusoren (axial-radial) an Dampfturbinen
US6261055B1 (en) * 1999-08-03 2001-07-17 Jerzy A. Owczarek Exhaust flow diffuser for a steam turbine
US6636320B1 (en) * 2000-10-18 2003-10-21 Lockheed Martin Corporation Fiber optic tufts for flow separation detection
US6896475B2 (en) * 2002-11-13 2005-05-24 General Electric Company Fluidic actuation for improved diffuser performance
EP1970539A1 (fr) * 2007-03-13 2008-09-17 Siemens Aktiengesellschaft Agencement de diffuseur
JP5309818B2 (ja) * 2008-09-10 2013-10-09 トヨタ自動車株式会社 気流状態監視装置

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4398865A (en) * 1978-11-10 1983-08-16 Garkusha Anatoly V Exhaust pipe of turbine
US20080063516A1 (en) * 2006-09-08 2008-03-13 Siemens Power Generation, Inc. Adjustable turbine exhaust flow guide and bearing cone assemblies
US20090068006A1 (en) * 2007-05-17 2009-03-12 Elliott Company Tilted Cone Diffuser for Use with an Exhaust System of a Turbine

Also Published As

Publication number Publication date
EP2598725A1 (fr) 2013-06-05
US20130121806A1 (en) 2013-05-16
WO2012013529A1 (fr) 2012-02-02
CN103026009A (zh) 2013-04-03
JP2013532793A (ja) 2013-08-19
CN103026009B (zh) 2015-08-12
JP5551316B2 (ja) 2014-07-16
EP2598725B1 (fr) 2015-01-07

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