EP0595692A1 - Gasabfuhrdiffusor für eine Gas Turbine - Google Patents

Gasabfuhrdiffusor für eine Gas Turbine Download PDF

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Publication number
EP0595692A1
EP0595692A1 EP93402592A EP93402592A EP0595692A1 EP 0595692 A1 EP0595692 A1 EP 0595692A1 EP 93402592 A EP93402592 A EP 93402592A EP 93402592 A EP93402592 A EP 93402592A EP 0595692 A1 EP0595692 A1 EP 0595692A1
Authority
EP
European Patent Office
Prior art keywords
section
sheath
bulb
square section
gas turbine
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.)
Granted
Application number
EP93402592A
Other languages
English (en)
French (fr)
Other versions
EP0595692B1 (de
Inventor
Jacques Poux
Liberto Gandia
Frédéric Rouget
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.)
European Gas Turbines SA
Original Assignee
European Gas Turbines SA
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 European Gas Turbines SA filed Critical European Gas Turbines SA
Publication of EP0595692A1 publication Critical patent/EP0595692A1/de
Application granted granted Critical
Publication of EP0595692B1 publication Critical patent/EP0595692B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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

Definitions

  • the present invention relates to a gas turbine exhaust diffuser.
  • the gases from the gas turbines leave the last expansion stage with very high speed. It is necessary to considerably reduce this speed before discharging the gases into the atmosphere so as to ensure the reliability of the exhaust material by reducing the stresses due to flow, to promote the performance of the turbomachine by limiting the loss of flow charge and to be able to adequately process the noise emitted by the exhaust of the turbomachine.
  • the dimensioning of the sheaths and of the diffusing members is also of a significant economic impact, especially when the sizes of the machines increase as currently and the compactness of the exhaust sheaths is another essential parameter for the realization of a system of evacuation of the high performance gas.
  • this circular section duct In general, the outlet of this circular section duct must be connected to a square section duct in order to obtain a duct which can be used for the installation of silent devices and also to obtain a compactness. overall sheaths. This transition limits the possibility of correctly diffusing the gases, in a stable manner and with homogeneous velocity profiles.
  • the present invention provides a diffuser intended to be interposed between the outlet of the circular section sheath and the inlet of a sheath of square section of silent devices for example which solves any problem of instability of the flow.
  • each fin consists of a sheet in the form of a quadrilateral with perpendicular diagonals folded along its largest diagonal to have a cross section in V, the opening of the V being turned towards the internal wall of said sheaths.
  • the largest folded diagonal is disposed inclined, its upstream end being close to the end of the bulb, distant from the axis of symmetry of the transition sheath by a distance slightly greater than the radius of the bulb, and its downstream end being disposed near the corners of the square section.
  • Figure 1 is a perspective view of the diffuser according to the invention mounted downstream of a last stage of gas turbine, seen downstream of the flow.
  • Figure 2 is a perspective view of the diffuser according to the invention mounted downstream of a last stage of gas turbine, seen from upstream of the flow.
  • Figure 3 is a longitudinal sectional view of the diffuser according to the invention mounted on a last stage of a gas turbine, showing the flow of gases.
  • the exhaust diffuser for a gas turbine is inserted downstream of a final expansion stage consisting of a sheath 1 of circular section comprising a central bulb 2, cylindrical of section decreasing at its end.
  • the sheaths 1,3 are reinforced in a known manner by stiffeners 9 welded to their external wall.
  • the fins 4 are preferably fixed by welding bars not shown in FIGS. 1 and 2 and referenced by the reference 10 in FIG. 3, welded to each fin 4 and to the internal wall of the transition sheath 3.
  • Each fin 4 consists of a sheet in the form of a quadrilateral with perpendicular diagonals folded along its largest diagonal 5 to have a cross section in V, the opening of the V being turned towards the internal wall of said sheaths 1,3.
  • the largest folded diagonal 5 is disposed inclined, its upstream end 6 being near the end of the bulb 2, distant from the axis of symmetry 8 of the transition sheath 3 by a distance slightly greater than the radius of the bulb 2, and its downstream end 7 being disposed near the corners of the square section.
  • the resulting gas diffusion is shown in Figure 3.
  • the downstream flow 11 is of annular section around the bulb 2. Arriving at the end of the bulb 3, instead of entering a particularly unstable, it is guided by the fins 4 which diffuses it in a practically perfect manner over the entire surface 12 of the square section of the transition sheath 3, by directing it in particular at the corners thereof.
  • fins 4 part of the energetic and stable fluid at the end of the bulb 2 is taken to be directed towards the corners of maximum diffusion.
  • These fins 4 discharge the gases both progressively on the sides of the square section and inject a part of these into the corners of the square section, via the transition sheath 3.
  • these fins 4 makes it possible to obtain, a few meters downstream, the stability of the idle fluid, this for a fairly large range of angles of incidence of the flow on them, of approximately plus or minus 30 °.
  • this diffuser makes it possible to obtain very good flow velocity distributions, a few meters downstream, the ratio of the average speed over the theoretical speed being approximately plus or minus 30%.
  • this diffuser generates little pressure drop, linked to the performance of the gas turbine, and makes it possible, in a small footprint, to obtain a performance gain much greater than said losses.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP93402592A 1992-10-26 1993-10-22 Gasabfuhrdiffusor für eine Gas Turbine Expired - Lifetime EP0595692B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9212724 1992-10-26
FR9212724A FR2697287B1 (fr) 1992-10-26 1992-10-26 Diffuseur d'échappement de turbine à gaz.

Publications (2)

Publication Number Publication Date
EP0595692A1 true EP0595692A1 (de) 1994-05-04
EP0595692B1 EP0595692B1 (de) 1996-06-05

Family

ID=9434843

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93402592A Expired - Lifetime EP0595692B1 (de) 1992-10-26 1993-10-22 Gasabfuhrdiffusor für eine Gas Turbine

Country Status (4)

Country Link
US (1) US5462088A (de)
EP (1) EP0595692B1 (de)
DE (1) DE69302989T2 (de)
FR (1) FR2697287B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2934009A1 (fr) * 2008-07-21 2010-01-22 Ge Energy Products France Snc Diffuseur d'echappement pour turbine a gaz
CN103032171A (zh) * 2011-10-03 2013-04-10 通用电气公司 排气扩散器

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
TW504546B (en) * 2000-10-17 2002-10-01 Fisher & Amp Paykel Ltd A linear compressor
US6896475B2 (en) * 2002-11-13 2005-05-24 General Electric Company Fluidic actuation for improved diffuser performance
WO2007019336A2 (en) * 2005-08-04 2007-02-15 Rolls-Royce Corporation, Ltd. Gas turbine exhaust diffuser
US20090280008A1 (en) 2008-01-16 2009-11-12 Brock Gerald E Vorticity reducing cowling for a diffuser augmented wind turbine assembly
US20090280009A1 (en) * 2008-01-16 2009-11-12 Brock Gerald E Wind turbine with different size blades for a diffuser augmented wind turbine assembly
US20090180869A1 (en) * 2008-01-16 2009-07-16 Brock Gerald E Inlet wind suppressor assembly
US8257025B2 (en) * 2008-04-21 2012-09-04 Siemens Energy, Inc. Combustion turbine including a diffuser section with cooling fluid passageways and associated methods
US8337153B2 (en) * 2009-06-02 2012-12-25 Siemens Energy, Inc. Turbine exhaust diffuser flow path with region of reduced total flow area
US8668449B2 (en) * 2009-06-02 2014-03-11 Siemens Energy, Inc. Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow
US8647057B2 (en) * 2009-06-02 2014-02-11 Siemens Energy, Inc. Turbine exhaust diffuser with a gas jet producing a coanda effect flow control
US20110236201A1 (en) * 2010-03-23 2011-09-29 Sumedhkumar Vyankatesh Shende Method and apparatus for radial exhaust gas turbine
DE202010016820U1 (de) * 2010-12-21 2012-03-26 Ebm-Papst Mulfingen Gmbh & Co. Kg Diffusor für einen Ventilator sowie Ventilatoranordnung mit einem derartigen Diffusor
US20130087632A1 (en) * 2011-10-11 2013-04-11 Patrick Germain Gas turbine engine exhaust ejector nozzle with de-swirl cascade
DE102012003336A1 (de) * 2012-02-17 2013-08-22 Ziehl-Abegg Ag Diffusor, Ventilator mit einem solchen Diffusor sowie Gerät mit solchen Ventilatoren
US9822664B1 (en) 2013-03-14 2017-11-21 Calpine Corporation Turbine exhaust cylinder baffle seal and method for installing turbine exhaust cylinder baffle seal
WO2014175763A1 (en) 2013-04-25 2014-10-30 Siemens Aktiengesellschaft Turbo-machine and waste heat utilization device
EP2918791A1 (de) * 2014-03-13 2015-09-16 Siemens Aktiengesellschaft Zur Führung eines Heißgases vorgesehene Vorrichtung sowie Verwendung von Formsand
EP2947283B1 (de) 2014-05-23 2017-01-11 GE Energy Products France SNC Thermoakustische Dämmstruktur für die Abgasanlage einer sich drehenden Maschine
DE102014114798A1 (de) 2014-10-13 2016-04-14 Thermofin Gmbh Axialventilator mit Außen- und Innendiffusor
DE102015213625A1 (de) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Diffusorbauteil für eine Gasturbine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1940790A (en) * 1930-10-18 1933-12-26 Walter S Diehl Fluid conducting passage
US3909156A (en) * 1974-02-28 1975-09-30 Westinghouse Electric Corp Gas turbine having exhaust bearing support struts

Family Cites Families (11)

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GB191400036A (en) * 1913-01-02 1915-07-22 Fortuna Werke Albert Hirth Improvements in Mountings for Cylindrical Knives or Skiving Machines.
US3095697A (en) * 1956-02-07 1963-07-02 Boeing Co Noise suppression nozzles with thrust reversal provision for jet engines
US3134655A (en) * 1960-08-23 1964-05-26 Du Pont Apparatus and method for steampolymer separation
US3191380A (en) * 1963-05-10 1965-06-29 Boeing Co Jet noise suppressor
FR1481950A (fr) * 1965-12-13 1967-05-26 Bertin & Cie Perfectionnements apportés aux dispositifs d'éjection de gaz
US3533561A (en) * 1968-09-11 1970-10-13 Harold P Henderson Sprinkler head
US3613996A (en) * 1969-07-03 1971-10-19 Rohr Corp Ejector with suppressor chutes
US4497345A (en) * 1981-11-04 1985-02-05 Lees Jeremy J Flow conversion device and method
US4753780A (en) * 1983-09-26 1988-06-28 Phillips Petroleum Company Atomizing feed for cracking unit
US4619138A (en) * 1984-12-19 1986-10-28 Buford Ohnhaus Airflow measurement shroud
US5099879A (en) * 1991-05-16 1992-03-31 Coen Company, Inc. Combustion air flow stabilizer

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1940790A (en) * 1930-10-18 1933-12-26 Walter S Diehl Fluid conducting passage
US3909156A (en) * 1974-02-28 1975-09-30 Westinghouse Electric Corp Gas turbine having exhaust bearing support struts

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2934009A1 (fr) * 2008-07-21 2010-01-22 Ge Energy Products France Snc Diffuseur d'echappement pour turbine a gaz
WO2010010277A1 (fr) * 2008-07-21 2010-01-28 Ge Energy Products France Snc Diffuseur d'echappement pour turbine a gaz
DE112009001754T5 (de) 2008-07-21 2011-07-28 Ge Energy Products France Snc Abgasdiffusor für Gasturbine
CN103032171A (zh) * 2011-10-03 2013-04-10 通用电气公司 排气扩散器

Also Published As

Publication number Publication date
DE69302989T2 (de) 1996-10-31
DE69302989D1 (de) 1996-07-11
US5462088A (en) 1995-10-31
FR2697287B1 (fr) 1994-12-09
EP0595692B1 (de) 1996-06-05
FR2697287A1 (fr) 1994-04-29

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