US20100226767A1 - Diffuser arrangement - Google Patents

Diffuser arrangement Download PDF

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Publication number
US20100226767A1
US20100226767A1 US12/596,244 US59624408A US2010226767A1 US 20100226767 A1 US20100226767 A1 US 20100226767A1 US 59624408 A US59624408 A US 59624408A US 2010226767 A1 US2010226767 A1 US 2010226767A1
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US
United States
Prior art keywords
flow
diffuser
guiding device
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.)
Abandoned
Application number
US12/596,244
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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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MAEHLMANN, STEFAN, BROEKER, MARC, BECKER, SASCHA, STANKA, ULRICH, HOFFACKER, RALF, KOEBE, MARIO
Publication of US20100226767A1 publication Critical patent/US20100226767A1/en
Abandoned 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
    • 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 refers to a diffuser arrangement and especially to an exhaust steam plenum of a steam turbine or an exhaust gas plenum of a gas turbine with the diffuser arrangement.
  • a diffuser is a passage which is exposable to throughflow by fluid and which in the case of separation-free throughflow decelerates the fluid by means of cross-sectional widening and, in accordance with Bernoulli's theorem, reduces the kinetic pressure of the fluid to the benefit of the static pressure.
  • the quality of the diffuser is described by means of the pressure recovery coefficient, which is defined by
  • Diffusers are used for example in pipelines for pressure recovery or for constant bridging of cross-sectional widenings (transition diffuser).
  • the diffusers are axially symmetrically formed.
  • FIG. 4 a longitudinal section of an axially symmetrical diffuser 101 is shown, and schematically shows the flow which typically occurs within it.
  • the diffuser 101 has an inlet cross section 102 and an outlet cross section 103 , the area ratio of which is greater than one.
  • a cylindrical inflow pipe is arranged, through which flows an inflow 108
  • a cylindrical outflow pipe is arranged, through which flows an outflow 109 .
  • the static pressure in the boundary layer is constant transversely to the flow direction.
  • the flow velocity of the flow close to the wall decreases. After negotiating a specific flow path the gradient of the flow velocity transversely to, and on, the diffuser wall is zero. This position is a separation point 105 of the flow, which is shown in the boundary layer profile 113 .
  • the flow moves away from the diffuser wall towards the middle of the diffuser 101 , wherein downstream of the separation point 105 in the wall proximity a backflow develops which forms a separation bubble 106 .
  • the separation bubble 106 brings about a narrowing of the cross section of the diffuser 101 which is effectively exposed to throughflow so that the main flow in the region of the separation bubble 106 is accelerated. As a result, in the main flow the kinetic energy is increased and the flow is reapplied in the outlet pipe at a reapplication point 107 .
  • the degree of opening of the diffuser 101 which is shown in FIG. 4 substantially determines the shape and the size of the separation bubble 106 and the position of the separation point 105 and of the reapplication point 107 which possibly occurs.
  • the higher the degree of opening of the diffuser 101 the further upstream the separation point 105 lies.
  • the separation bubble 106 reduces the pressure recovery effect of the diffuser 101 compared with a diffuser in which the flow is fully applied.
  • a bladed wheel which is seated on a hub, the blades of which, being shrouded by a diffuser plate, are connected on the blade tip side by means of a ring, is known from laid-open specification DE 1 628 337.
  • a ring of stator blades is arranged on the ring in such a way that this widens the jet flow which flows off the bladed wheel while maintaining the boundary flow which is guided by the diffuser plate.
  • this is especially achieved by the ring having a corresponding cross-sectional shape which, moreover, benefits the course of the entrained flow filaments and blows these out at higher velocity.
  • a pipe which is arranged parallel to the diffuser wall and which extends along the flow direction is known from JP 08 260905.
  • the flow cross section of the annular passage which is formed between diffuser wall and the pipe is increased so that medium flowing in the annular passage is decelerated.
  • a steam turbine or a gas turbine is run at partial load, base load and overload.
  • their individual components can be geometrically designed in an optimized manner only at a single operating point for example with regard to efficiency or aerodynamic or thermodynamic effectiveness. This has the result that at other operating points, which are not identical to the design operating point, the components cannot operate in an optimum manner.
  • the exhaust steam plenum or the exhaust gas plenum is conventionally constructed as an axial diffuser.
  • the axial diffuser is geometrically designed in an optimized manner with regard to the base load so that at partial load and overload the axial diffuser cannot be operated in an optimized manner.
  • the mass flow of the flow which flows through the axial diffuser is lower in the partial load range than in the base load range, as a result of which the average flow velocity in the axial diffuser in the base load range is higher than in the partial load range.
  • the flow in the axial diffuser in the partial load range is more prone to separation than the flow which occurs in the axial diffuser at base load.
  • a reduction of the degree of opening of the axial diffuser could provide a remedy in this case since the flow is decelerated less sharply as a result and is therefore prone to separation to a lesser degree.
  • the overall length of the axial diffuser is consequently extended, as a result of which the total overall length of the steam turbine or gas turbine is disadvantageously increased.
  • the diffuser arrangement according to the invention is exposable to throughflow by fluid and has an outer diffuser which has an inner surface, and a flow-accelerating device which is installed in such a way that at least some of the boundary layer flow which develops 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 is prevented.
  • the fluid flows through the outer diffuser, then it is decelerated in the main flow direction, as a result of which the boundary layer flow which develops on the inner surface of the outer diffuser is principally prone to separation.
  • the separation would emanate from a point at which the kinetic energy of the flow is zero.
  • the flow-accelerating device By means of the flow-accelerating device according to the invention at least some of the flow close to the wall is accelerated so that the kinetic energy of the flow close to the wall is increased. As a result, the effect of the kinetic energy of the flow close to the wall not being zero at any point is prevented, as a result of which a flow separation on the inner surface of the outer diffuser is prevented. Therefore, the diffuser arrangement has a high pressure recovery.
  • the outer diffuser of the diffuser arrangement can have a large degree of opening without a flow separation occurring in it. Consequently, the outer diffuser and therefore the diffuser arrangement has a shorter overall length.
  • the flow-accelerating device has a flow guiding device which extends inside the outer diffuser, and by its outer surface, which faces the inner surface of the outer diffuser, and a section of the inner surface of the outer diffuser, forms a nozzle passage through which the part of the boundary layer flow can flow.
  • the flow-accelerating device is formed by the nozzle passage which is defined by the flow guiding device interacting with the inner wall of the outer diffuser.
  • the extent of the flow-guiding device in the main flow direction lies in the region of 5% to 40% of the extent in the main flow direction of the outer diffuser.
  • the flow-guiding device is arranged entirely inside the outer diffuser and can be accurately placed on any section on the inner wall of the outer diffuser on which a separation of the fluid flow is to be expected. Therefore, the flow-guiding device can be purposefully arranged on a section where separation is a risk, as a result of which an effective prevention of flow separation is achieved and therefore the disturbance of the main flow by the flow-guiding device is low.
  • the flow-guiding device by its inner surface which faces away from the outer surface forms an inner diffuser through which the fluid flow can flow and in so doing can be decelerated in the main flow direction.
  • the flow-guiding device in addition to the nozzle effect in the outer region the flow-guiding device also has a diffuser effect in the inner region so that the flow through the diffuser arrangement is sharply decelerated.
  • the effect is achieved of the pressure recovery of the diffuser arrangement according to the invention being high.
  • the outer diffuser and the flow-guiding device are axially symmetrically formed and are concentrically arranged around a common symmetry axis.
  • the nozzle passage is formed as an annular passage.
  • the diffuser arrangement is advantageously created as an arrangement of a plurality of diffusers and a nozzle.
  • This arrangement is formed by a series-connecting of the three diffusers, specifically the region of the outer diffuser upstream of the flow-guiding device, the inner diffuser of the flow-guiding device, and the region of the outer diffuser downstream of the flow-guiding device, and a parallel-connecting of the nozzle passage to the inner diffuser of the flow-guiding device.
  • the flow-guiding device is preferably formed as a straight guide plate.
  • the guide plate can advantageously be cost-effectively produced.
  • the flow-guiding device is aerodynamically profiled. Consequently, the flow-guiding device has a low flow resistance.
  • the flow-guiding device is arranged in the region of 80% to 100% of the passage height (radius) of the outer diffuser.
  • the flow-guiding device is advantageously effectively placed in the flow close to the wall and, as a result, is aerodynamically effectively placed.
  • the flow-guiding device is preferably arranged in the region of the inlet cross section of the outer diffuser.
  • the flow-guiding device is pivotably mounted relative to the main flow.
  • the effect is advantageously achieved of the flow-guiding device being able to be individually adjusted by pivoting with regard to the respective flow conditions inside the outer diffuser in such a way that the flow-guiding device is aerodynamically effective.
  • An exhaust steam plenum of a steam turbine or an exhaust gas plenum of a gas turbine preferably features the diffuser arrangement according to the invention.
  • the flow-accelerating 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 exemplary embodiment of the diffuser arrangement
  • FIG. 2 shows a longitudinal section through a second exemplary embodiment of the diffuser arrangement
  • FIG. 3 shows a longitudinal section through a third exemplary embodiment of the diffuser arrangement
  • FIG. 4 shows a longitudinal section of a diffuser with schematic representation of the flow conditions.
  • a diffuser arrangement 1 has an outer diffuser 2 which is axially symmetrically formed around its symmetry axis 3 .
  • An inlet cross section 4 of the outer diffuser 2 through which an inflow 5 flows into the outer diffuser 2 , lies in a plane which is perpendicular to the symmetry axis 3
  • its outlet cross section 6 from which an outflow 7 discharges from the outer diffuser 2 , lies in another plane which is perpendicular to the symmetry axis 3 of the outer diffuser 2 .
  • This outer diffuser has an inner surface 8 which delimits the inside space of the said outer diffuser 2 .
  • the outer diffuser 2 is formed as a straight diffuser, i.e. the inner surface 8 of the outer diffuser 2 forms a truncated cone, wherein the cross-sectional area at the inlet cross section 4 is smaller than the cross-sectional area at the outlet cross section 6 .
  • a flow-guiding device 9 is arranged inside the outer diffuser 2 .
  • the flow-guiding device 9 is formed as a guide plate which is oblong in longitudinal section and which, axially-symmetrically arranged around the symmetry axis 3 of the outer diffuser 2 concentrically with the outer diffuser 2 , delimits a truncated cone-shaped annular passage which narrows in the flow direction.
  • the flow-guiding device 9 On its outer periphery the flow-guiding device 9 has an outer surface 10 which with regard to the inner surface 8 of the outer diffuser 2 is inclined in such a way that the annulus cross section decreases in the flow direction in a plane which is perpendicular to the symmetry axis 3 and formed between the flow-guiding device 9 and the outer diffuser 2 .
  • the outer surface 10 of the flow-guiding device 9 interacts with a section of the inner surface 8 of the outer diffuser 2 which lies opposite it in such a way that the annular passage, which lies between the flow-guiding device 9 and the outer diffuser 2 , forms a nozzle passage 11 . Therefore, the section 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 passage 11 .
  • the flow-guiding device 9 Upstream, the flow-guiding device 9 is delimited by its leading edge 13 and downstream is delimited by its trailing edge 14 .
  • An inlet cross section 15 of the nozzle passage 11 is located in the region from the leading edge 13 of the flow-guiding device 9 up to the inner surface 8 of the outer diffuser 2
  • the outlet cross section 16 of the nozzle passage 11 is located in the region of the trailing edge 14 of the flow-guiding device 9 up to the inner surface 8 of the outer diffuser 2 , wherein the cross-sectional area of the inlet cross section 15 is greater than the cross-sectional area of the outlet cross section 16 .
  • 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-guiding device 9 is arranged in a plane which is perpendicular to the symmetry axis 3 and forms an inlet cross section 19 of the inner diffuser 18
  • the trailing edge 14 of the flow-guiding device 9 is arranged in a plane which is 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 effectiveness of the flow-guiding device 9 is evident.
  • the flow-guiding device 9 is formed as a profiled annular guide plate.
  • flow lines 21 are drawn 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 also a velocity profile 24 downstream of the flow-guiding device 9 are shown.
  • the flow lines 21 have a converging path in the main flow direction, as a result of which the flow acceleration which is induced by means of the flow-guiding device 9 is indicated.
  • the velocity gradient, which is normal to the wall, on the inner surface 8 of the outer diffuser 2 is flatter in the case of the velocity profile 22 upstream of the flow-guiding device 9 than in the case of the velocity profile 23 at the trailing edge 14 of the flow-guiding device 9 , which is flatter than the velocity gradient, which is normal to the wall, of the velocity profile 24 downstream of the flow-guiding device 9 .
  • the flow-guiding device 9 which is guided by the flow-guiding device 9 through the nozzle passage 11 , is accelerated (energized). Therefore, the flow-guiding device 9 locally increases the velocity of the flow in the proximity of the inner surface 12 of the outer diffuser 2 .
  • high-energy flow material from the core flow is deflected in the direction towards the inner surface 12 of the outer diffuser 2 and therefore is added to the boundary layer on the inner surface 12 of the outer diffuser 2 .
  • the boundary layer on the inner surface 12 of the outer diffuser 2 can overcome greater positive pressure gradients in the main flow direction without being separated from the inner surface 12 of the outer diffuser 2 in the process.
  • the outer diffuser 2 reacts kindly to premature separation phenomena. Therefore, by provision of the flow-guiding device 9 in the outer diffuser 2 a higher pressure recovery of the outer diffuser 2 is achieved.
  • FIG. 3 shows an exhaust gas plenum 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 guides away the outflow, which issues 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 , recovering pressure.
  • the turbine rotor 25 has a turbine rotor hub 26 which is continued by a cylindrical outer diffuser hub 27 with the turbine rotor hub 26 .
  • the turbine rotor 25 has a multiplicity of turbine rotor blades 28 which on their radial outer ends have a blade tip 29 .
  • the turbine rotor 25 is enclosed by a turbine casing 30 .
  • a gap 31 is provided between the turbine rotor blade tip 29 and the turbine casing 30 so that the turbine rotor blade tip 29 does not rub on the turbine casing 30 during operation of the turbine rotor 25 .
  • a minimum distance as a gap 31 is necessary between rotor blade 28 and casing 30 .
  • Some of the mass flow can flow through this gap without power yield to the rotor blade 28 and leads to energizing of the boundary layer.
  • mass flow can flow through to a greater or lesser extent.
  • a further energizing of the boundary layer by means of the flow-guiding device 9 is desired.
  • a remedy is provided by arranging the flow-guiding device 9 close to the inner surface 8 of the outer diffuser 2 in the region of the inlet cross section of the outer diffuser 4 .
  • the boundary layer which is disturbed by the leakage flow is accelerated in the main flow direction by the flow-guiding device 9 on the inner surface of the outer diffuser 2 so that the kinetic energy in this flow region is increased.
  • the effect is achieved of the flow not separating in the outer diffuser 2 on the inner surface 8 of the outer diffuser 2 . Therefore, the flow losses in the outer diffuser 2 are low and the pressure recovery of the outer diffuser 2 is high.

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  • 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)
US12/596,244 2007-03-13 2008-02-25 Diffuser arrangement Abandoned US20100226767A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP07005175.0 2007-03-13
EP07005175A EP1970539A1 (de) 2007-03-13 2007-03-13 Diffusoranordnung
PCT/EP2008/052222 WO2008110445A1 (de) 2007-03-13 2008-02-25 Diffusoranordnung

Publications (1)

Publication Number Publication Date
US20100226767A1 true US20100226767A1 (en) 2010-09-09

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Application Number Title Priority Date Filing Date
US12/596,244 Abandoned US20100226767A1 (en) 2007-03-13 2008-02-25 Diffuser arrangement

Country Status (5)

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

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JP2012207565A (ja) * 2011-03-29 2012-10-25 Mitsubishi Heavy Ind Ltd タービン排気構造及びガスタービン
US20130101387A1 (en) * 2011-10-20 2013-04-25 General Electric Company System and method for integrating sections of a turbine
US20130121806A1 (en) * 2010-07-26 2013-05-16 Alexander R. Beeck Exhaust diffuser for a gas turbine, and method thereof
US20140003931A1 (en) * 2012-06-28 2014-01-02 Alstom Technology Ltd Diffuser for the exhaust section of a gas turbine and gas turbine with such a diffuser
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
US20160230573A1 (en) * 2015-02-05 2016-08-11 Alstom Technology Ltd. Steam turbine diffuser configuration
US20160312649A1 (en) * 2015-04-21 2016-10-27 Siemens Energy, Inc. High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry
US20160341053A1 (en) * 2015-05-22 2016-11-24 General Electric Company Turbomachine diffuser including flow mixing lobes and method
WO2016190760A1 (en) * 2015-05-22 2016-12-01 General Elctric Company Flow mixing lobe and corresponding method of forming
US20170254222A1 (en) * 2016-03-07 2017-09-07 General Electric Company Gas turbine exhaust diffuser with air injection
WO2021153556A1 (ja) * 2020-01-31 2021-08-05 三菱重工業株式会社 タービン
WO2022201932A1 (ja) * 2021-03-24 2022-09-29 三菱パワー株式会社 タービン、及びガスタービン

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EP2224101A1 (de) * 2009-02-27 2010-09-01 Siemens Aktiengesellschaft Gasturbine
EP2407638A1 (de) 2010-07-15 2012-01-18 Siemens Aktiengesellschaft Abgasdiffusor für eine Gasturbine und Verfahren zum Betreiben einer Gasturbine mit einem solchen Abgasdiffusor
EP2410139A1 (de) 2010-07-19 2012-01-25 Siemens Aktiengesellschaft Abgasdiffusor für eine Gasturbine
DE102013204006A1 (de) * 2013-03-08 2014-09-11 Siemens Aktiengesellschaft Diffusoranordnung für ein Abdampfgehäuse einer Dampfturbine, sowie damit ausgestattete Dampfturbine
WO2014175763A1 (en) * 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Turbo-machine and waste heat utilization device
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
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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US9845689B2 (en) 2011-03-29 2017-12-19 Mitsubishi Heavy Industries, Ltd. Turbine exhaust structure and gas turbine
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US9404391B2 (en) * 2012-06-28 2016-08-02 General Electric Technology Gmbh Diffuser for the exhaust section of a gas turbine and gas turbine with such a diffuser
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US20160230573A1 (en) * 2015-02-05 2016-08-11 Alstom Technology Ltd. Steam turbine diffuser configuration
US20160312649A1 (en) * 2015-04-21 2016-10-27 Siemens Energy, Inc. High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry
US10329945B2 (en) * 2015-04-21 2019-06-25 Siemens Energy, Inc. High performance robust gas turbine exhaust with variable (adaptive) exhaust diffuser geometry
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JP2018519456A (ja) * 2015-05-22 2018-07-19 ゼネラル・エレクトリック・カンパニイ 流れ混合ローブおよび対応する形成方法
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US10344604B2 (en) * 2015-05-22 2019-07-09 General Electric Company Turbomachine diffuser including flow mixing lobes and method
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US10883387B2 (en) * 2016-03-07 2021-01-05 General Electric Company Gas turbine exhaust diffuser with air injection
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JP2021124021A (ja) * 2020-01-31 2021-08-30 三菱重工業株式会社 タービン
CN115003898A (zh) * 2020-01-31 2022-09-02 三菱重工业株式会社 涡轮机
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JP7368260B2 (ja) 2020-01-31 2023-10-24 三菱重工業株式会社 タービン
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WO2022201932A1 (ja) * 2021-03-24 2022-09-29 三菱パワー株式会社 タービン、及びガスタービン

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CN101680305A (zh) 2010-03-24
RU2009137901A (ru) 2011-04-20

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