EP0076668B1 - Turbomaschinen mit einer Entlüftungsvorrichtung - Google Patents

Turbomaschinen mit einer Entlüftungsvorrichtung Download PDF

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Publication number
EP0076668B1
EP0076668B1 EP82305243A EP82305243A EP0076668B1 EP 0076668 B1 EP0076668 B1 EP 0076668B1 EP 82305243 A EP82305243 A EP 82305243A EP 82305243 A EP82305243 A EP 82305243A EP 0076668 B1 EP0076668 B1 EP 0076668B1
Authority
EP
European Patent Office
Prior art keywords
turbine
air
turbo
diffuser
exhaust gas
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.)
Expired
Application number
EP82305243A
Other languages
English (en)
French (fr)
Other versions
EP0076668A3 (en
EP0076668A2 (de
Inventor
Jan Mowill
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.)
Kongsberg Gruppen ASA
Original Assignee
Kongsberg Vapenfabrikk AS
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
Priority claimed from US06/309,239 external-priority patent/US4459802A/en
Application filed by Kongsberg Vapenfabrikk AS filed Critical Kongsberg Vapenfabrikk AS
Publication of EP0076668A2 publication Critical patent/EP0076668A2/de
Publication of EP0076668A3 publication Critical patent/EP0076668A3/en
Application granted granted Critical
Publication of EP0076668B1 publication Critical patent/EP0076668B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/08—Adaptations for driving, or combinations with, pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/601—Fluid transfer using an ejector or a jet pump

Definitions

  • the present invention relates to a turbo- machine such as a turbo-charger or a gas turbine engine having a compressor assembly including a labyrinth seal, and a turbine assembly including an exhaust gas diffuser.
  • a bleedoff of working medium may also be used for obtaining a given pressure recovery with a shorter diffuser length, whereby the diffuser will be lighter and probably also cheaper.
  • a bleedoff of boundary layers has a beneficial effect on most types of diffusers, but the effect is especially large in stepped diffusers as indicated above.
  • the object of the present invention is to provide a simple method of effecting the bleedoff of working medium from exhaust gas diffusers in turbo-machinery in such a manner that the total efficiency can be improved to such an extent that a bleedoff of working medium constitutes a more attractive and interesting possibility.
  • the invention is based upon the recognition that the unavoidable leakage of compressed air through a labyrinth seal in the compressor may be combined with the bleeding of fluid working medium from boundary layers of vortex regions of the exhaust gas diffuser in an advantageous manner to give a substantially improved total efficiency.
  • the leakage air may be used directly to provide a removal of working medium from the low pressure region of the exhaust gas diffuser. Leakage air leaking through a labyrinth seal of the compressor is bled off and its energy used to draw off by suction part of the working medium from said exhaust gas diffuser.
  • a turbo-machine of the kind defined hereinbefore is characterised in that it comprises an energy conversion means which is operated by compressed air leaking through said labyrinth seal and supplies energy for removing working medium by suction from a boundary layer or vortex flow in said exhaust gas diffuser, said energy conversion means comprising a first conduit connected at one end to the low pressure side of said labyrinth seal of said compressor assembly to receive air leaking through said seal, and connected at the other end to a suction means, a second conduit connected at one end to the suction inlet of said suction means and connected at the other end to said boundary layer or vortex flow of said exhaust gas diffuser.
  • a bleedoff is especially effective in stepped diffusers, since the bleeding may be effected from a single area close to the step in the flow path, and the present invention is therefore especially useful in connection with such diffusers.
  • a stepped diffuser with bleedoff may provide a pressure recovery of about 90% compared with about 60% for an ordinary linear conical diffuser.
  • a pressure recovery or efficiency of above 60% may also be obtained with conical diffusers without bleedoff if consisting of a series of coaxially placed diffusers.
  • this involves a far more expensive and mechanically complicated design which is seldom used.
  • In order to obtain a pressure recovery of about 90% it may be necessary to bleedoff approximately 1-3% of the working medium, but it may also be possible to manage with smaller amounts.
  • the aerodynamic gains may provide a total improvement of the efficiency in the order of 10%. In the case of a gas turbine this may result in a corresponding reduction of the fuel consumption.
  • the use of stepped diffusers is believed also to provide substantial practical advantages with respect to manufacturing costs.
  • a good exhaust gas diffuser will be of especial significance to the total thermal efficiency.
  • the importance of the invention is believed to be especially great for medium and small turbo-machinery such as turbo-chargers and gas turbines for use in propelling machinery in e.g. automobiles, since the boundary layers in such small machines occupy a comparatively large part of the flow passages, thereby resulting in a rather large reduction of the efficiency.
  • the internal utilisation of the energy in the compressed leakage air according to the invention will therefore provide an especially large increase of the efficiency in small machinery, so that the disadvantage of a low efficiency inherent in such small turbo-machinery may be reduced.
  • a compressor 1 which through a compressor diffuser 2 supplies compressed air to a combustion chamber 7.
  • the gases from the combustion chamber are passed to a turbine 3 having a stepped exhaust gas diffuser 4.
  • the turbine 3 drives the compressor 1.
  • the turbine 3 generates substantially more energy than required for driving the compressor 1 and also supplies energy for operating a further load, e.g. an electric power generator which is not shown.
  • Compressed air leaking through a conventional labyrinth seal 5 of the compressor 1 is bled off through a conduit 6 which leads to an air turbine 8 operating a pump or compressor 9 for removing working medium by suction from the vortex flow in the stepped exhaust gas diffuser 4.
  • an ejector operated by the leakage air to produce the suction required to remove working medium from the diffuser 4.
  • the use of an ejector provides the best results when the air from the compressor 1 and the working medium from the diffuser 4 have approximately the same density.
  • ejectors may still be preferable in connection with small machines, since they have various other advantages such as low costs.
  • the bleedoff of air from the compressor 1 may also be combined with a cooling of hot parts of the machinery, said air being used for cooling prior to utilizing the energy in the air in connection with a bleedoff from the exhaust gas diffuser.
  • a cooling of hot parts of the machinery said air being used for cooling prior to utilizing the energy in the air in connection with a bleedoff from the exhaust gas diffuser.
  • Fig. 2 shows schematically on a larger scale the labyrinth seal through which the compressed air flows before it reaches the conduit 6.
  • Leakage of higher than atmospheric pressure air through clearances between rotating and static parts of a turbo-machine is unavoidable.
  • 0.5% to 2% of the air has normally to be bled from the engine cycle and this represents a performance penalty.
  • this air is too hot to be used as bearing seal air.
  • the present invention uses this "lost" air to control the boundary layer in the turbine exhaust diffuser.
  • air from the exit portion of a compressor 1 leaks through labyrinth seals generally indicated at 5. At the outer portion of the seals 5 this normally wasted leaking air is bled off through the conduit 6 and fed to an ejector inlet line (not shown) or to the inlet of an air turbine as shown at 8 in Fig. 1.
  • the invention can use the compressor leakage air either as primary air in a jetpump or ejector or to drive a compressor 9 which thus pumps the subatmospheric air out from the exhaust gas diffuser 4.
  • the predicted improvement in exhaust diffuser performance is large enough to provide a net improvement in power output and thermal efficiency in addition to make up for the lost air.
  • the working medium is air and combustion gases respectively, since the invention is illustrated in connection with turbo-chargers and turboshaft engines. However, a corresponding effect may be obtained in connection with other fluids.
  • the use of other working mediums, especially vapour and other gases, is therefore within the scope of the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)

Claims (3)

1. Turbo-Maschine, z.B. ein Turbolader oder eine Gasturbinenmaschine, mit einer Kompressoranordnung (1) mit einer Labyrinth-Dichtung (5), und mit einer Turbinenanordnung (3) mit einem Abgasdiffusor (4), gekennzeichnet durch einen Energiewandler, der mit Druckluft betrieben wird, die durch die Labyrinth-Dichtung (5) entweicht, und der Energie zum Abziehen von Arbeitsmedium durch Ansaugen von einer Grenzschicht oder Wirbelströmung in dem Abgasdiffusor (4) liefert, wobei der Energiewandler eine erste Leitung (6), die an einem Ende an die Niederdruckseite der Labyrinth-Dichtung (5) der Kompressoranordnung (1) angeschlossen ist, um durch die Dichtung (5) entweichende Luft aufzunehmen, und am anderen Ende an eine Saugeinrichtung (8, 9) angeschlossen ist, und eine zweite Leitung aufweist, die an einem Ende an den Saugeinlaß der Saugeinrichtung (8, 9) und am anderen Ende an die Grenzschicht oder die Wirbelströmung des Abgasdiffusors (4) angeschlossen ist.
2. Turbo-Maschine nach Anspruch 1, wobei die Saugeinrichtung eine Anordnung mit Hilfsgasturbine (8) und Pumpe (9) aufweist, wobei die Hilfsgasturbine (8) und die Pumpe (9) betriebsmäßig so verbunden sind, daß die Turbine (8) die Pumpe (9) antreibt, und wobei das andere Ende der ersten Leitung (6) mit dem Einlaß der Hilfsturbine (8) verbunden ist, um die Turbine (9) anzutreiben.
3. Turbo-Maschine nach Anspruch 1, wobei die Saugeinrichtung einen Düsenejektor aufweist.
EP82305243A 1981-10-06 1982-10-01 Turbomaschinen mit einer Entlüftungsvorrichtung Expired EP0076668B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US309239 1981-10-06
US06/309,239 US4459802A (en) 1978-01-02 1981-10-06 Bleedoff of gas diffusers in fluid flow machines

Publications (3)

Publication Number Publication Date
EP0076668A2 EP0076668A2 (de) 1983-04-13
EP0076668A3 EP0076668A3 (en) 1983-10-05
EP0076668B1 true EP0076668B1 (de) 1986-08-27

Family

ID=23197331

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82305243A Expired EP0076668B1 (de) 1981-10-06 1982-10-01 Turbomaschinen mit einer Entlüftungsvorrichtung

Country Status (3)

Country Link
EP (1) EP0076668B1 (de)
JP (1) JPS5879608A (de)
DE (2) DE3272914D1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8474266B2 (en) 2009-07-24 2013-07-02 General Electric Company System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5136837A (en) * 1990-03-06 1992-08-11 General Electric Company Aircraft engine starter integrated boundary bleed system
US5125597A (en) * 1990-06-01 1992-06-30 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed with energy recovery system
US5143329A (en) * 1990-06-01 1992-09-01 General Electric Company Gas turbine engine powered aircraft environmental control system and boundary layer bleed
US5137230A (en) * 1991-06-04 1992-08-11 General Electric Company Aircraft gas turbine engine bleed air energy recovery apparatus
GB9400555D0 (en) * 1994-01-13 1994-03-09 Short Brothers Plc Boundery layer control in aerodynamic low drag structures
EP0961033B1 (de) * 1998-05-25 2003-10-08 ABB Turbo Systems AG Radialverdichter
GB0004140D0 (en) 2000-02-23 2000-04-12 Holset Engineering Co Compressor
FR2835019B1 (fr) * 2002-01-22 2004-12-31 Snecma Moteurs Diffuseur pour moteur a turbine a gaz terrestre ou aeronautique
ATE458259T1 (de) 2005-09-26 2010-03-15 Abb Technology Ag Hochspannungsschalter mit verbesserter schaltleistung
US8313286B2 (en) * 2008-07-28 2012-11-20 Siemens Energy, Inc. Diffuser apparatus in a turbomachine
US20120186261A1 (en) * 2011-01-20 2012-07-26 General Electric Company System and method for a gas turbine exhaust diffuser

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR935783A (fr) * 1946-01-25 1948-06-30 Goetaverken Ab Perfectionnements aux compresseurs actionnés par des turbines
DE1938215A1 (de) * 1968-07-31 1970-02-05 Gen Electric Achsendichtungssystem fuer eine Dampfturbine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1199042A (fr) * 1958-05-28 1959-12-10 Bertin & Cie Perfectionnements apportés à l'alimentation en énergie des appareils à circuits pneumatiques
US3109285A (en) * 1959-08-03 1963-11-05 Boeing Co Accessory power system for aircraft
US3856430A (en) * 1973-07-27 1974-12-24 Gen Motors Corp Diffuser with boundary layer removal

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR935783A (fr) * 1946-01-25 1948-06-30 Goetaverken Ab Perfectionnements aux compresseurs actionnés par des turbines
DE1938215A1 (de) * 1968-07-31 1970-02-05 Gen Electric Achsendichtungssystem fuer eine Dampfturbine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8474266B2 (en) 2009-07-24 2013-07-02 General Electric Company System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle
US8893511B2 (en) 2009-07-24 2014-11-25 General Electric Company Systems and methods for a gas turbine combustor having a bleed duct

Also Published As

Publication number Publication date
EP0076668A3 (en) 1983-10-05
DE76668T1 (de) 1983-12-22
EP0076668A2 (de) 1983-04-13
JPS5879608A (ja) 1983-05-13
DE3272914D1 (en) 1986-10-02

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