EP2140112A1 - Dispositif diffuseur - Google Patents

Dispositif diffuseur

Info

Publication number
EP2140112A1
EP2140112A1 EP08717072A EP08717072A EP2140112A1 EP 2140112 A1 EP2140112 A1 EP 2140112A1 EP 08717072 A EP08717072 A EP 08717072A EP 08717072 A EP08717072 A EP 08717072A EP 2140112 A1 EP2140112 A1 EP 2140112A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
flow
outer diffuser
section
cross
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Withdrawn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
EP08717072A
Other languages
German (de)
English (en)
Inventor
Sascha Becker
Marc Bröker
Ralf Hoffacker
Mario Koebe
Stefan 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 EP08717072A priority Critical patent/EP2140112A1/fr
Publication of EP2140112A1 publication Critical patent/EP2140112A1/fr
Withdrawn legal-status Critical Current

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
    • 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.
  • the quality of the diffuser is described by the pressure recovery coefficient associated with
  • FIG. 4 shows a longitudinal section of an axially symmetrical diffuser 101 and schematically illustrates the flow typically occurring 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 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 degree of opening of the diffuser 101 shown in FIG. 4 decisively determines the shape and size of the peel-off bladder 106 and the location of the detachment point 105 and the optionally occurring reapplication point 107. The higher the degree of opening 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 compared to a diffuser in which the flow is fully applied.
  • Diffuser sheet coated leaves are connected blade-tip side by a ring.
  • a ring of vanes is arranged such that it widens the stream of air flowing from the blade wheel while maintaining the edge flow guided by the diffuser plate.
  • this is achieved in particular by the fact that the ring has a corresponding cross-sectional shape, which also favors the course of the entrained stream threads and blows them out at a higher speed.
  • a pipe arranged parallel to the diffuser wall is known, which extends along the flow direction. Due to the diverging cross section of the diffuser and the parallel, correspondingly diverging tube, the flow cross-section of the annular channel formed between the diffuser wall and the tube increases, so that the medium flowing in the annular channel is delayed.
  • a steam turbine or a gas turbine is driven at partial, basic and overload.
  • its individual components can be For example, be optimized in terms of efficiency or aerodynamic or thermodynamic efficiency optimized only in a single operating point geometrically. As a result, in other operating points that are not identical to the design operating point, the components can not operate optimally.
  • This situation also applies to an exhaust steam room of the steam turbine or an exhaust space of the gas turbine.
  • the exhaust steam space or the exhaust gas space is conventionally designed as an axial diffuser.
  • 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, as a result of which 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 is more prone to detachment than the flow which occurs at the base load in the axial diffuser.
  • a remedy here could be to reduce the opening degree of the axial diffuser, as this slows down the flow less and thus tends less to detach. However, this lengthens the overall length of the axial diffuser, which adversely increases the overall length of the steam turbine or gas turbine.
  • 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 acceleration 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 at the Inner surface of the outer diffuser is prevented.
  • the fluid flows through the outer diffuser, it is delayed 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 has a flow guide which extends inside 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 flow.
  • 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 immediately adjacent to the inner surface of the outer diffuser the wall-near flow, i. just the flow rate 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 extent in the main flow direction of the outer end fender.
  • 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 device can be arranged in a targeted manner to a detachment-prone area, whereby an effective prevention of flow separation is achieved and yet the disturbance of the main flow through the flow-guiding device 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 area of the outer diffuser upstream of the flow guide, the inner diffuser of the flow guide and the area 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 guide plate is advantageously producible at low cost.
  • the flow guide is aerodynamically profiled. As a result, 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 exhaust steam space of a steam turbine or an exhaust space 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.
  • FIG. 1 shows a longitudinal section through a first embodiment of the diffuser arrangement
  • Fig. 3 is a longitudinal section through a third embodiment of the diffuser assembly
  • FIG. 4 shows a longitudinal section of a diffuser with a schematic representation of the flow conditions.
  • a diffuser arrangement 1 has an outer diffuser 2, which is designed to be rotationally symmetrical about its axis of symmetry 3.
  • 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 from the
  • 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 an elongated in longitudinal section guide plate, which is rotationally symmetrical about the axis of symmetry of the 3 Exterior diffuser 2 arranged concentric with the
  • Outer diffuser 2 limits a frusto-conical annular channel, which tapers in the flow direction.
  • 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 lies between the flow guide 9 and the outer diffuser 2, a nozzle channel 11 is formed.
  • the portion of the inner surface 8 of the outer diffuser 2, which faces the outer surface 10 of the flow guiding device 9, is an inner surface 12 of the 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. In the region of the front edge 13 of the flow guide 9 to the inner surface 8 of the outer diffuser 2 is an inlet cross section 15 of the nozzle channel 11 and in the region of the trailing edge 14 of the flow guide 9 to the inner surface 8 of the outer diffuser 2 is the outlet cross section 16 of the nozzle channel 11, wherein the cross-sectional area of the inlet cross-section 15 is greater than the cross-sectional area of the outlet cross-section 16.
  • the front 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 Conducting device 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 cross section 19 is smaller than the outlet cross section 20.
  • the aerodynamic efficiency of the flow guide 9 can be seen.
  • the flow guide 9 is formed as a profiled annular guide plate.
  • FIG. 2 shows flow lines 21 in the region of the flow-guiding device 9 and a velocity profile 22 upstream of the flow-guiding device 9, a velocity profile 23 at the trailing edge 14 of the flow-guiding device 9 and a velocity profile 24 downstream of the flow-guiding device 9 shown.
  • 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 flatter at the velocity profile upstream of the flow guide 9 than at 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 9.
  • 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.
  • this energy tion can overcome the boundary layer on the inner surface 12 of the outer diffuser 2 larger positive pressure gradient 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 gas space of a gas turbine, which is designed 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 multiplicity of turbine rotor blades 28 which have a blade tip 29 at their radial outer ends.
  • the turbine rotor 25 is surrounded by a turbine housing 30.
  • 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.

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)

Abstract

Un dispositif diffuseur (1) pouvant être traversé par un fluide présente un diffuseur externe (2) présentant une surface interne et un dispositif d'accélération de courant (3), qui est orienté de telle sorte qu'au moins une partie du courant de couche limite se formant sur la surface interne du diffuseur externe (8) est accélérable dans la direction du courant principal de telle sorte qu'un décollement de courant sur la surface interne du diffuseur externe (8) est empêché. En outre, un espace d'évaporation d'une turbine à vapeur ou un espace d'évaporation d'une turbine à gaz présente le dispositif diffuseur.
EP08717072A 2007-03-13 2008-02-25 Dispositif diffuseur Withdrawn EP2140112A1 (fr)

Priority Applications (1)

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

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07005175A EP1970539A1 (fr) 2007-03-13 2007-03-13 Agencement de diffuseur
EP08717072A EP2140112A1 (fr) 2007-03-13 2008-02-25 Dispositif diffuseur
PCT/EP2008/052222 WO2008110445A1 (fr) 2007-03-13 2008-02-25 Dispositif diffuseur

Publications (1)

Publication Number Publication Date
EP2140112A1 true EP2140112A1 (fr) 2010-01-06

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 Before (1)

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

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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
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
DE102013204006A1 (de) * 2013-03-08 2014-09-11 Siemens Aktiengesellschaft Diffusoranordnung für ein Abdampfgehäuse einer Dampfturbine, sowie damit ausgestattete Dampfturbine
WO2014175763A1 (fr) * 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Turbomachine et dispositif d'utilisation de chaleur perdue
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
US10760451B2 (en) 2015-05-22 2020-09-01 General Electric Company Manufacture and installation of diffuser flow mixing lobes
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
JP7368260B2 (ja) * 2020-01-31 2023-10-24 三菱重工業株式会社 タービン
KR20230133916A (ko) * 2021-03-24 2023-09-19 미츠비시 파워 가부시키가이샤 터빈, 및 가스 터빈
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

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Also Published As

Publication number Publication date
RU2009137901A (ru) 2011-04-20
EP1970539A1 (fr) 2008-09-17
CN101680305A (zh) 2010-03-24
US20100226767A1 (en) 2010-09-09
WO2008110445A1 (fr) 2008-09-18

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