EP1970539A1 - Agencement de diffuseur - Google Patents

Agencement de diffuseur Download PDF

Info

Publication number
EP1970539A1
EP1970539A1 EP07005175A EP07005175A EP1970539A1 EP 1970539 A1 EP1970539 A1 EP 1970539A1 EP 07005175 A EP07005175 A EP 07005175A EP 07005175 A EP07005175 A EP 07005175A EP 1970539 A1 EP1970539 A1 EP 1970539A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
flow
flow guide
arrangement
outer diffuser
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Withdrawn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
EP07005175A
Other languages
German (de)
English (en)
Inventor
Sascha Becker
Marc Bröker
Ralf Hoffacker
Mario Dr. Koebe
Stefan Dr. Mählmann
Ulrich Stanka
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 EP07005175A priority Critical patent/EP1970539A1/fr
Priority to RU2009137901/06A priority patent/RU2009137901A/ru
Priority to EP08717072A priority patent/EP2140112A1/fr
Priority to US12/596,244 priority patent/US20100226767A1/en
Priority to PCT/EP2008/052222 priority patent/WO2008110445A1/fr
Priority to CN200880015828.7A priority patent/CN101680305A/zh
Publication of EP1970539A1 publication Critical patent/EP1970539A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/0005—Baffle plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0025—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/02—Influencing flow of fluids in pipes or conduits
    • F15D1/06—Influencing flow of fluids in pipes or conduits by influencing the 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent

Definitions

  • the invention relates to a diffuser arrangement and more particularly to an exhaust steam room of a steam turbine or an exhaust gas space of a gas turbine with the diffuser arrangement.
  • a diffuser is a fluid-permeable channel which delays the fluid in a transfer-free flow through cross-sectional widening and according to Bernoulli's theorem reduces the kinetic pressure of the fluid in favor of the static pressure.
  • diffusers are used in pipelines for pressure recovery or for continuous bridging of cross-sectional extensions (transitional diffuser).
  • the diffusers are formed axially symmetrical.
  • Fig. 4 a longitudinal section of an axisymmetric diffuser 101 is shown and shown schematically the flow occurring typically therein.
  • the diffuser 101 has an inlet cross section 102 and an outlet cross section 103, whose area ratio is greater than one. Upstream of the diffuser 101, a cylindrical inflow pipe is arranged, through which an inflow 108 flows, and downstream of the diffuser 101 a cylindrical outflow pipe is arranged, through which an outflow 109 flows.
  • the static pressure of the flow in the flow direction increases correspondingly, satisfying the first law of thermodynamics.
  • the static pressure in the boundary layer is constant across the flow direction.
  • the flow velocity of the near-wall flow decreases. After overcoming a certain flow path, the gradient of the flow velocity across and against the diffuser wall is zero. This location is a separation point 105 of the flow shown in the boundary layer profile 113.
  • the flow moves away from the diffuser wall toward the center of the diffuser 101, forming a return flow downstream of the separation point 105 near the wall forming a detachment bladder 106.
  • the detachment bladder 106 causes a constriction of the effective cross-section of the diffuser 101, so that the main flow in the region of the detachment bladder 106 is accelerated. As a result, the kinetic energy increases in the main flow and the flow settles in the outlet pipe at a restart point 107 again.
  • the opening degree of the diffuser 101 largely determines the shape and size of the peel-off bubble 106 and the location of the peel-off point 105 and the optionally occurring reapplication point 107. The higher the opening degree of the diffuser 101, the further upstream the detachment point 105 is.
  • the peel bladder 106 reduces the pressure recovery effect of the diffuser 101 as compared to a diffuser in which the flow is fully applied.
  • a steam turbine or a gas turbine is driven at partial, basic and overload.
  • the steam turbine or gas turbine whose individual components can be optimized geometrically optimized, for example, in terms of efficiency or aerodynamic or thermodynamic effectiveness only in a single operating point.
  • the components can not operate optimally.
  • the axial diffuser is optimally designed geometrically with regard to the base load so that the axial diffuser can not be optimally operated with partial and overload.
  • the mass flow of the flow flowing through the axial diffuser is smaller in the partial load range than in the base load range, whereby the mean flow velocity in the axial diffuser is higher in the base load range than in the partial load range.
  • the flow in the axial diffuser in the partial load range tends to be more detachable than the flow which occurs in the axial diffuser at base load.
  • the object of the invention is to provide a diffuser arrangement whose pressure recovery is high and whose overall length is small.
  • Fluid can flow through the diffuser arrangement according to the invention and has an outer diffuser having an inner surface and a flow accelerating device which is set up in such a way that at least part of the boundary layer flow forming on the inner surface of the outer diffuser can be accelerated in the main flow direction, so that a flow separation on the inner surface of the outer diffuser Outside diffusers is prevented.
  • the fluid flows through the outer diffuser, it is retarded in the main flow direction, whereby the boundary layer flow which forms on the inner surface of the outer diffuser tends in principle to detach.
  • the detachment would come from a place where the kinetic energy of the flow is zero.
  • the flow acceleration device By means of the flow acceleration device according to the invention, at least part of the wall-near flow is accelerated, so that the kinetic energy of the wall-near flow is increased. Thereby, it is prevented that the kinetic energy of the near-wall flow is zero at any location, whereby a flow separation is prevented on the inner surface of the outer diffuser.
  • the diffuser assembly has a high pressure recovery.
  • the outer diffuser of the diffuser assembly may have a large degree of opening without flow separation occurring therein. As a result, the outer diffuser and thus the diffuser arrangement has a smaller overall length.
  • the flow acceleration device preferably has a flow guide which extends within the outer diffuser and with its outer surface facing the inner surface of the outer diffuser and a section of the inner surface of the outer diffuser forms a nozzle channel through which the part of the boundary layer flow can be flowed.
  • the flow accelerating means is constituted by the nozzle passage defined by the flow guide in cooperation with the inner wall of the outer diffuser. It is thereby achieved that directly on the inner surface of the outer diffuser the near-wall flow, ie just the flow component with otherwise low kinetic energy, is accelerated. This effectively prevents separation in the diffuser arrangement.
  • the flow guiding device with its inner surface facing away from the outer surface, form an inner diffuser, through which the fluid flow can be flowed and thereby retarded in the main flow direction.
  • the flow-guiding device in addition to the nozzle effect in the outer region, also has a diffuser effect in the inner region, so that the flow through the diffuser arrangement is greatly delayed. This ensures that the pressure recovery of the diffuser assembly according to the invention is high.
  • the extent of the flow guide in the main flow direction is in the range of 5% to 40% of the extension in the main flow direction of the outer diffuser.
  • the flow-guiding device is arranged completely within the outer diffuser and can be placed exactly at that region on the inner wall of the outer diffuser, at which a detachment of the fluid flow is to be expected.
  • the flow directing can be targeted to a detachment vulnerable area, whereby an effective suppression of flow separation is achieved and yet the disturbance of the main flow through the flow guide is low.
  • the outer diffuser and the flow guide are formed axially symmetrical and are arranged concentrically about a common axis of symmetry.
  • the nozzle channel is formed as an annular channel.
  • the diffuser assembly advantageously results as an array of multiple diffusers and a nozzle.
  • This arrangement is formed by a series connection of the three diffusers, namely the region of the outer diffuser upstream of the flow guide, the inner diffuser of the Flow guiding device and the region of the outer diffuser downstream of the flow guide, and a parallel connection of the nozzle channel with the inner diffuser of the flow guide.
  • the flow guide is designed as a straight baffle.
  • the baffle is advantageously produced inexpensively.
  • the flow guide is aerodynamically profiled.
  • the flow guide has a low flow resistance.
  • the flow-guiding device is arranged in the range from 80% to 100% of the channel height (radius) of the outer diffuser.
  • the flow-guiding device is advantageously effective in the near-wall flow and thereby placed aerodynamically effective.
  • the flow-guiding device is preferably arranged in the region of the inlet cross-section of the outer diffuser.
  • the inlet flow into the outer diffuser of the flow guiding device to already have an accelerated flow in the boundary layer region, which thus does not tend to detach in the course along the inner surface of the outer diffuser.
  • the flow-guiding device is mounted pivotably relative to the main flow.
  • An evaporation chamber of a steam turbine or an exhaust gas chamber of a gas turbine preferably has the diffuser arrangement according to the invention.
  • the flow acceleration device is arranged on the inner surface of the outer diffuser in the region of its inlet.
  • a diffuser assembly 1 on an outer diffuser 2 which is formed around its axis of symmetry 3 rotationally symmetrical.
  • an inlet cross-section 4 of the outer diffuser 2 In a plane perpendicular to the axis of symmetry 3 is an inlet cross-section 4 of the outer diffuser 2, through which an inflow 5 flows into the outer diffuser 2, and in another plane perpendicular to the symmetry axis 3 of the outer diffuser 2 is its outlet cross-section 6, from which an outflow 7 emerges from the outer diffuser 2.
  • Limiting the interior of the outer diffuser 2 this has an inner surface 8.
  • the outer diffuser 2 is designed as a straight diffuser, i. the inner surface 8 of the outer diffuser 2 forms a truncated cone, the cross-sectional area at the inlet cross-section 4 being smaller than the cross-sectional area at the outlet cross-section 6.
  • the flow guide 9 is formed as a guide plate, which is rotationally symmetrical about the symmetry axis 3 of the outer diffuser 2 arranged concentrically with the outer diffuser 2 forms a truncated cone, which tapers upstream.
  • the flow guide 9 has on its outer periphery an outer surface 10 which is inclined relative to the inner surface 8 of the outer diffuser 2 such that the annular space cross-section in a plane perpendicular to the symmetry axis 3, which is formed between the flow guide 9 and the outer diffuser 2, in the flow direction downsized.
  • the outer surface 10 of the flow guide 9 cooperates with an opposite portion of the inner surface 8 of the outer diffuser 8 such that the annular channel, which is located between the flow guide 9 and the outer diffuser 2, forms a nozzle channel 11.
  • the flow guide 9 Upstream, the flow guide 9 is bounded by its front edge 13 and downstream of its trailing edge 14.
  • this Facing away from the outer surface 10 of the flow-guiding device 9, this has an inner surface 17 which forms an inner diffuser 18.
  • the leading edge 13 of the flow guide 9 is arranged in a plane perpendicular to the symmetry axis 3 and forms an inlet cross section 19 of the inner diffuser 18 and the trailing edge 14 of the flow guide 9 is arranged in a plane perpendicular to the symmetry axis 3 and forms an outlet cross section 20 of the inner diffuser 18, wherein the Inlet section 19 is smaller than the outlet cross-section 20 is.
  • the aerodynamic efficiency of the flow guide 9 can be seen.
  • the flow guide 9 is formed as a profiled annular guide plate.
  • the streamlines 21 have a convergent course in the main flow direction, as a result of which the flow acceleration caused by the flow-guiding device 9 is indicated.
  • the wall normal velocity gradient on the inner surface 8 of the outer diffuser 2 is upstream of the flow guide 9 in the velocity profile flatter than the velocity profile 23 at the trailing edge 14 of the flow guide 9, which is shallower than the wall normal velocity gradient of the velocity profile 24 downstream of the flow device 9th
  • the flow which is conducted by the flow-guiding device 9 through the nozzle channel 11 is accelerated (energized).
  • the flow guide 9 locally increases the velocity of the flow in the vicinity of the inner surface 12 of the outer diffuser 2.
  • high-energy flow material from the core flow is directed toward the inner surface 12 of the outer diffuser 2 and thus the boundary layer on the inner surface 12 of the outer diffuser 2 supplied.
  • the boundary layer on the inner surface 12 of the outer diffuser 2 can overcome larger positive pressure gradients in the main flow direction without detaching from the inner surface 12 of the outer diffuser 2.
  • the outer diffuser 2 reacts more benignly against premature detachment.
  • a high pressure recovery of the outer diffuser 2 is achieved.
  • Fig. 3 shows an exhaust space of a gas turbine, which is formed as the outer diffuser 2.
  • the outer diffuser 2 is arranged downstream of a turbine rotor 25 and continues the outflow emerging from the turbine rotor 25 from the inlet cross section 4 of the outer diffuser 2 to the outlet cross section 6 of the outer diffuser 2 under pressure recovery.
  • the turbine rotor 25 has a turbine rotor hub 26, which is continued by a cylindricalfactendiffusornabe 27 with the turbine rotor hub 26.
  • the turbine rotor 25 has a plurality of turbine rotor blades 28 which at their radial outer ends a Have blade tip 29.
  • the turbine rotor 25 is surrounded by a turbine housing 30. In operation, the turbine rotor 25 rotates about its axis of rotation (not shown) while the turbine housing 30 remains stationary. Therefore, a gap 31 is provided between the turbine rotor blade tip 29 and the turbine housing 30 so that the turbine rotor blade tip 29 does not touch the turbine housing 30 during operation of the turbine rotor 25.
  • Fig. 3 is provided by arranging the flow guide 9 near the inner surface 8 of the outer diffuser 2 in the region of the inlet cross section of the outer diffuser 4 remedy.
  • the boundary layer disturbed by the leakage flow is accelerated by the flow guide 9 on the inner surface of the outer diffuser 8 in the main flow direction, so that the kinetic energy in this flow area is increased.
  • This ensures that the flow in the outer diffuser 2 does not detach on the inner surface 8 of the outer diffuser 2.
  • the flow losses in the outer diffuser 2 are low and the pressure gain of the outer diffuser 2 is high.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Jet Pumps And Other Pumps (AREA)
EP07005175A 2007-03-13 2007-03-13 Agencement de diffuseur Withdrawn EP1970539A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP07005175A EP1970539A1 (fr) 2007-03-13 2007-03-13 Agencement de diffuseur
RU2009137901/06A RU2009137901A (ru) 2007-03-13 2008-02-25 Диффузорное устойство
EP08717072A EP2140112A1 (fr) 2007-03-13 2008-02-25 Dispositif diffuseur
US12/596,244 US20100226767A1 (en) 2007-03-13 2008-02-25 Diffuser arrangement
PCT/EP2008/052222 WO2008110445A1 (fr) 2007-03-13 2008-02-25 Dispositif diffuseur
CN200880015828.7A CN101680305A (zh) 2007-03-13 2008-02-25 扩压装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07005175A EP1970539A1 (fr) 2007-03-13 2007-03-13 Agencement de diffuseur

Publications (1)

Publication Number Publication Date
EP1970539A1 true EP1970539A1 (fr) 2008-09-17

Family

ID=38329988

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07005175A Withdrawn EP1970539A1 (fr) 2007-03-13 2007-03-13 Agencement de diffuseur
EP08717072A Withdrawn EP2140112A1 (fr) 2007-03-13 2008-02-25 Dispositif diffuseur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08717072A Withdrawn EP2140112A1 (fr) 2007-03-13 2008-02-25 Dispositif diffuseur

Country Status (5)

Country Link
US (1) US20100226767A1 (fr)
EP (2) EP1970539A1 (fr)
CN (1) CN101680305A (fr)
RU (1) RU2009137901A (fr)
WO (1) WO2008110445A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2224101A1 (fr) * 2009-02-27 2010-09-01 Siemens Aktiengesellschaft Turbine à gaz
EP2407638A1 (fr) 2010-07-15 2012-01-18 Siemens Aktiengesellschaft Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement
EP2410139A1 (fr) 2010-07-19 2012-01-25 Siemens Aktiengesellschaft Diffuseur de gaz d'échappement pour une turbine à gaz
WO2014175763A1 (fr) * 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Turbomachine et dispositif d'utilisation de chaleur perdue
RU2575212C2 (ru) * 2010-07-15 2016-02-20 Сименс Акциенгезелльшафт Диффузор отходящего газа для газовой турбины, газовая турбина с таким диффузором и способ работы такой газовой турбины
EP2775096A3 (fr) * 2013-03-08 2018-02-21 Siemens Aktiengesellschaft Diffuseur pour un carter d'échappement d'une turbine à vapeur et turbine à vapeur équipée d'un tel diffuseur
CN114508394A (zh) * 2021-12-29 2022-05-17 东方电气集团东方汽轮机有限公司 一种透平抽汽腔室结构
CN115003898A (zh) * 2020-01-31 2022-09-02 三菱重工业株式会社 涡轮机

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2412941A1 (fr) * 2010-07-26 2012-02-01 Siemens Aktiengesellschaft Diffuseur d'échappement pour une turbine à gaz et procédé correspondant
US9249687B2 (en) * 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
JP5951187B2 (ja) * 2011-03-29 2016-07-13 三菱重工業株式会社 タービン排気構造及びガスタービン
US9284853B2 (en) * 2011-10-20 2016-03-15 General Electric Company System and method for integrating sections of a turbine
EP2679780B8 (fr) * 2012-06-28 2016-09-14 General Electric Technology GmbH Diffuseur pour section d'échappement d'une turbine à gaz et turbine à gaz dotée d'un tel diffuseur
EP3054086B1 (fr) * 2015-02-05 2017-09-13 General Electric Technology GmbH Configuration de diffuseur de turbine à vapeur
US10329945B2 (en) * 2015-04-21 2019-06-25 Siemens Energy, Inc. High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry
WO2016190760A1 (fr) * 2015-05-22 2016-12-01 General Elctric Company Lobe de mélange d'écoulement et procédé de formation correspondant
JP2016217355A (ja) * 2015-05-22 2016-12-22 ゼネラル・エレクトリック・カンパニイ 流れ混合ローブを含むターボ機械ディフューザ及びその方法
US10883387B2 (en) * 2016-03-07 2021-01-05 General Electric Company Gas turbine exhaust diffuser with air injection
DE102017121337A1 (de) * 2017-09-14 2019-03-14 Abb Turbo Systems Ag Diffusor einer abgasturbine
US10718264B2 (en) * 2018-03-16 2020-07-21 The Boeing Company Inlet diffusers for jet engines, jet engines, jet aircraft, and methods for diffusing incoming air of jet engines
CN113123838B (zh) * 2019-12-30 2023-05-30 上海汽轮机厂有限公司 一种排汽缸及其应用的汽轮机
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 (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1628337A1 (de) * 1966-09-26 1971-08-19 Nord Aviat Soc Nat De Const Ae Umkleidetes Zerstauber-Schaufelrad
DE2946368A1 (de) * 1978-11-17 1980-05-29 Tno Diffusor fuer ein fluides medium, der insbesondere einen grossen scheitelwinkel aufweist
DE2953333C1 (de) * 1978-11-27 1983-11-24 Char'kovskij politechničeskij institut imeni V.I. Lenina, Char'kov Turbinenabdampfstutzen
JPH08260905A (ja) * 1995-03-28 1996-10-08 Mitsubishi Heavy Ind Ltd 軸流タービン用排気ディフューザ
EP1178183A2 (fr) * 2000-07-31 2002-02-06 Alstom (Switzerland) Ltd Turbine à vapeur à basse pression avec un diffuseur à canaux multiples
DE10255389A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Niederdruckdampfturbine mit Mehrkanal-Diffusor

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1291943A (en) * 1970-02-11 1972-10-04 Secr Defence Improvements in or relating to ducted fans

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1628337A1 (de) * 1966-09-26 1971-08-19 Nord Aviat Soc Nat De Const Ae Umkleidetes Zerstauber-Schaufelrad
DE2946368A1 (de) * 1978-11-17 1980-05-29 Tno Diffusor fuer ein fluides medium, der insbesondere einen grossen scheitelwinkel aufweist
DE2953333C1 (de) * 1978-11-27 1983-11-24 Char'kovskij politechničeskij institut imeni V.I. Lenina, Char'kov Turbinenabdampfstutzen
JPH08260905A (ja) * 1995-03-28 1996-10-08 Mitsubishi Heavy Ind Ltd 軸流タービン用排気ディフューザ
EP1178183A2 (fr) * 2000-07-31 2002-02-06 Alstom (Switzerland) Ltd Turbine à vapeur à basse pression avec un diffuseur à canaux multiples
DE10255389A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Niederdruckdampfturbine mit Mehrkanal-Diffusor

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2224101A1 (fr) * 2009-02-27 2010-09-01 Siemens Aktiengesellschaft Turbine à gaz
EP2407638A1 (fr) 2010-07-15 2012-01-18 Siemens Aktiengesellschaft Diffuseur de gaz d'échappement pour un turbine à gaz et procédé de fonctionnement d'une turbine à gaz dotée d'un tel diffuseur de gaz d'échappement
WO2012007499A1 (fr) 2010-07-15 2012-01-19 Siemens Aktiengesellschaft Diffuseur d'échappement pour turbine à gaz et procédé de fonctionnement d'une turbine à gaz équipée d'un diffuseur d'échappement de ce type
RU2575212C2 (ru) * 2010-07-15 2016-02-20 Сименс Акциенгезелльшафт Диффузор отходящего газа для газовой турбины, газовая турбина с таким диффузором и способ работы такой газовой турбины
US9297390B2 (en) 2010-07-15 2016-03-29 Siemens Aktiengesellschaft Exhaust gas diffuser for a gas turbine and a method for operating a gas turbine that comprises such an exhaust gas diffuser
EP2410139A1 (fr) 2010-07-19 2012-01-25 Siemens Aktiengesellschaft Diffuseur de gaz d'échappement pour une turbine à gaz
EP2775096A3 (fr) * 2013-03-08 2018-02-21 Siemens Aktiengesellschaft Diffuseur pour un carter d'échappement d'une turbine à vapeur et turbine à vapeur équipée d'un tel diffuseur
WO2014175763A1 (fr) * 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Turbomachine et dispositif d'utilisation de chaleur perdue
CN115003898A (zh) * 2020-01-31 2022-09-02 三菱重工业株式会社 涡轮机
CN114508394A (zh) * 2021-12-29 2022-05-17 东方电气集团东方汽轮机有限公司 一种透平抽汽腔室结构
CN114508394B (zh) * 2021-12-29 2023-11-10 东方电气集团东方汽轮机有限公司 一种透平抽汽腔室结构

Also Published As

Publication number Publication date
RU2009137901A (ru) 2011-04-20
CN101680305A (zh) 2010-03-24
US20100226767A1 (en) 2010-09-09
WO2008110445A1 (fr) 2008-09-18
EP2140112A1 (fr) 2010-01-06

Similar Documents

Publication Publication Date Title
EP1970539A1 (fr) Agencement de diffuseur
EP0581978B1 (fr) Diffuseur à zones multiples pour turbomachine
DE60320537T2 (de) Kompressor mit schaufelspitzeneinrichtung
DE69311876T2 (de) Enteisungssystem
EP2725194B1 (fr) Aube de rotor d'une turbine à gaz
DE102015219556A1 (de) Diffusor für Radialverdichter, Radialverdichter und Turbomaschine mit Radialverdichter
DE60309272T2 (de) Diffusor mit Grenzschichteinblasung für einen Brennkammereinlass
EP2577071B1 (fr) Canal à surface de guidage d'écoulement
CH688867A5 (de) Axialdurchstroemte Turbine.
DE102010037047A1 (de) Stark umlenkende Diffusorstrebe mit Überströmschlitzen
CH701954B1 (de) Grundkörper eines Abgasdiffusors für ein Gasturbinensystem.
EP2378072A2 (fr) Canal en dérivation d'un turboréacteur
DE4422700A1 (de) Diffusor für Turbomaschine
DE1964057A1 (de) Kompressor
DE2707063A1 (de) Mischer fuer eine fan-triebwerksanlage
DE2853340A1 (de) Vorrichtung zum erzeugen eines vorwirbels am verdichtereingang eines turbinen-triebwerkes
DE112012002923B4 (de) Radialverdichter
EP1632648A2 (fr) Passage d'une turbomachine
DE102011106959A1 (de) Fluggasturbine mit variabler Nebenstromdüse
DE2801119A1 (de) Einrichtung zum verhindern des brummens bei ueberschalleinlaeufen fuer luftatmende rueckstosstriebwerke,insbesondere staustrahltriebwerke
DE102012003902A1 (de) Einlauf für eine Gasturbine
DE102011012039A1 (de) Kanal mit Strömungsleitfläche
EP3164578A1 (fr) Zone d'évacuation d'une turbine d'un turbocompresseur à gaz d'échappement
EP3321589A1 (fr) Buse de carburant d'une turbine à gaz dotée du générateur de tourbillons
DE102017118950A1 (de) Diffusor für einen Radialverdichter

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

AKX Designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20090318

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566