EP0589745A1 - Einlassregelanlage einer Turbomaschine - Google Patents

Einlassregelanlage einer Turbomaschine Download PDF

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Publication number
EP0589745A1
EP0589745A1 EP93402171A EP93402171A EP0589745A1 EP 0589745 A1 EP0589745 A1 EP 0589745A1 EP 93402171 A EP93402171 A EP 93402171A EP 93402171 A EP93402171 A EP 93402171A EP 0589745 A1 EP0589745 A1 EP 0589745A1
Authority
EP
European Patent Office
Prior art keywords
adjustment system
compressor
blades
control system
orifice
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
EP93402171A
Other languages
English (en)
French (fr)
Other versions
EP0589745B1 (de
Inventor
Pierre Biscay
Alain Jean-Pierre Farrando
Philippe Denis Joubert
Jean-Bernard Martin
Hubert Hippolyte Vignau
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.)
Safran Helicopter Engines SAS
Original Assignee
Turbomeca 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 Turbomeca SA filed Critical Turbomeca SA
Publication of EP0589745A1 publication Critical patent/EP0589745A1/de
Application granted granted Critical
Publication of EP0589745B1 publication Critical patent/EP0589745B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the present invention relates to a system for adjusting the air supply conditions of a turbomachine.
  • the invention relates in particular to an adjustment system for an air intake system of a centrifugal compressor, and more particularly of the external centrifugal compressor of an auxiliary power unit to a gas turbine.
  • the invention is more particularly applicable in the case of an annular pipe generally used in turbomachinery, and in particular in the suction part of compressors, and which allows these machines to suck directly, or through a plenum, the ambient air to properly supply their axial inlet part.
  • means for adjusting the supply conditions of the tubomachine such as guide vanes, are arranged around the axis of the machine and at regular intervals over a given diameter. .
  • blades arranged in a crown, are generally of variable angular setting and they can be oriented simultaneously between two extreme positions.
  • the adjustment system makes it possible to significantly reduce the flow rate which passes through the compressor and therefore the power required to drive it.
  • control means and the actuating cylinder are then of a complex and costly structure.
  • the guide vanes are in the fully closed, or almost complete, position and it is necessary to partially disassemble the air intake device to perform an endoscopic inspection of certain organs of the group. auxiliary power, and for example compressor blades. This inspection also requires the ability to control, when the turbomachine is stopped, the adjustment system, in order to bring the blades into their so-called fully open position.
  • the object of the invention is to propose an adjustment system of the type mentioned above which makes it possible to simultaneously remedy the drawbacks which have just been mentioned.
  • the invention provides an adjustment system comprising a series of guide vanes mounted movable between an open position and a closed position of an air inlet pipe of the turbomachine, characterized in that at least one of the blades has a through hole which passes through the profiled body of the blade.
  • the invention also provides a centrifugal compressor characterized in that it comprises an air intake system produced in accordance with the teachings of the invention.
  • the invention also provides an auxiliary power unit with a gas turbine, characterized in that it comprises an external centrifugal load compressor whose air intake system is equipped with an adjustment system produced in accordance with the teachings of the 'invention.
  • FIG. 1 represents a diagram of an auxiliary power unit with a gas turbine comprising an external charge compressor which can be equipped with an adjustment system according to the invention.
  • Figure 2 is a half sectional view of a charge compressor of an auxiliary power unit equivalent to that shown in Figure 1 and equipped with a system according to the invention.
  • FIG. 3 is a half-view in section of an air inlet pipe of the charge compressor illustrated in FIG. 2.
  • Figure 4 is a half cross-sectional view of the annular duct of the charge compressor, along line 4-4 of Figure 3, and in which the guide vanes are shown in the fully open position.
  • Figure 5 is a view similar to that of Figure 4, but in which the guide vanes are shown in the fully closed position.
  • Figure 6 is a view similar to those of Figures 4 and 5, but in which the guide vanes are shown in an intermediate position corresponding to a gyratory flow downstream thereof.
  • Figure 7 is a perspective view of a guide vane having an orifice for communicating its upper surface with its lower surface, corresponding to an embodiment of the invention.
  • auxiliary power units with gas turbine finds particular application in the case of auxiliary power units with gas turbine, as will be described in more detail below, but of course, they can be used in other turbomachinery or industrial devices having for example a compressor with one or more stages, fitted with variable-pitch guide vanes, such as turboshaft engines, turbopropellers, turbochargers, auxiliary power units with bleed power, etc.
  • this compressor can be of the axial, radial or mixed type.
  • the air inlet can be radial, axial or mixed.
  • Figure 1 there is shown by way of example a diagram of an auxiliary power unit with a gas turbine, comprising a charge compressor equipped with an adjustment system according to the invention.
  • this assembly designated by the general reference 1 comprises a turboshaft engine 2 shown diagrammatically in the area delimited by a contour in phantom.
  • This turbine engine 2 is used to drive a charge compressor 3 supplying compressed air to an accessory pneumatic assembly, such as for example an air conditioning system 4 of an airplane or to other devices actuated by compressed air such as pneumatic turbine engines or the like.
  • an accessory pneumatic assembly such as for example an air conditioning system 4 of an airplane or to other devices actuated by compressed air such as pneumatic turbine engines or the like.
  • the turbine engine 2 is also suitable for driving an electric generator 5.
  • a drive shaft 6 which comprises, for example, a reduction gear of the conventional type (not shown).
  • the burnt gases 11 are expanded in a two-stage axial turbine 12 to supply the desired power to the drive shaft 6, before being ejected into the atmosphere through an exhaust nozzle 13 disposed downstream of the turbine.
  • the rotation of the shaft 6 drives the power compressor 8, the charge compressor 3, the electric generator 5 and possibly other accessories.
  • the compressor has an annular air inlet pipe 14 making it possible to draw air into a plenum 15 and to feed a centrifugal mobile 16.
  • the centrifugal mobile 16 comprises a series of blades 17 making it possible to transform the mechanical energy transmitted by the drive shaft 6 into pneumatic energy.
  • Air leaks at the top of the movable blades 17 are limited by a static cover 18.
  • the charge compressor also comprises a diffusion assembly consisting of a diffuser 19, a radial diffuser with blades 20 and a volute 21 which is intended to supply compressed air to the pneumatic assembly 4 mentioned above.
  • the ambient air designated by the general reference 22 in FIG. 2
  • the ambient air is drawn into the supply plenum 15 over the entire periphery of the air inlet.
  • the radial flow of the air is then transformed into an axial flow in order to supply the centrifugal mobile 16 suitably.
  • the air 22 is compressed by the blades 17 in rotation and is delivered tangentially into the diffusion assembly.
  • the kinetic energy of the air leaving the mobile 16 is then transformed into pressure in the smooth diffuser 19 and in the radial diffuser with blades 20.
  • the air is collected in the volute 21 to be sent to the pneumatic assembly 4.
  • Means for adjusting the supply conditions of the compressor are also provided for adjusting the air flow rate and the pressure level supplied to the pneumatic assembly 4.
  • the blades 24 are arranged in a crown on the radial part of the gas inlet, at regular intervals, on a control diameter centered on the axis 25 of the machine.
  • the vanes 24 are of variable setting and can be oriented simultaneously by means of control shafts 26 and an auxiliary mechanical control assembly 28.
  • the conditions can be precisely adjusted. compressor power supply, and therefore adapt the flow rate and the pressure level supplied to the various components supplied by this compressor.
  • the adjustment system makes it possible to significantly reduce the air flow passing through the compressor and therefore the power necessary to drive it through the shaft 6 of the turbine engine 2.
  • At least one blade 24 has an orifice 27 for communicating its upper surface with its lower surface.
  • the orifice 27 can be produced in the form of a longitudinal through slot, that is to say which extends in the middle part of the guide vane 24 substantially along the longitudinal direction of gas flow along the blade.
  • Ports 27 for communication can be provided in all of the guide vanes, in a single vane, in two diametrically opposite vanes, in three vanes arranged at 120 ° relative to each other, or in any other configuration of blades.
  • the orifices are inoperative due to the small pressure difference existing between the lower and upper surfaces of the guide vanes.
  • the adjustment system according to the invention is particularly simple to carry out insofar as it requires no additional mechanical member and it also allows a slight reduction in the mass of the system.
  • the endoscopic inspection is carried out very simply, in the fully closed position, by introducing the endoscope through an orifice 27.
  • the gyratory movement imposed on the gas flow downstream of the guide vanes 24 can cause undesirable aerodynamic noise because noise annoyance caused to the immediate environment, due to the corresponding loss of energy inside the annular pipe and due to the risks of vibratory excitation of the mechanical parts placed near this pipe.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
EP93402171A 1992-09-25 1993-09-07 Einlassregelanlage einer Turbomaschine Expired - Lifetime EP0589745B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9211457A FR2696210B1 (fr) 1992-09-25 1992-09-25 Système de réglage des conditions d'alimentation en air d'une turbomachine, compresseur centrifuge comportant un système de réglage et groupe auxiliaire de puissance comportant un tel compresseur.
FR9211457 1992-09-25

Publications (2)

Publication Number Publication Date
EP0589745A1 true EP0589745A1 (de) 1994-03-30
EP0589745B1 EP0589745B1 (de) 1998-04-29

Family

ID=9433896

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93402171A Expired - Lifetime EP0589745B1 (de) 1992-09-25 1993-09-07 Einlassregelanlage einer Turbomaschine

Country Status (6)

Country Link
US (1) US5484261A (de)
EP (1) EP0589745B1 (de)
JP (1) JP2728356B2 (de)
CA (1) CA2106270C (de)
DE (2) DE69318242T2 (de)
FR (1) FR2696210B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0719944A2 (de) * 1994-12-28 1996-07-03 Ebara Corporation Turbomaschine mit Strömungsleiteinrichtungen mit variablem Winkel
US7305826B2 (en) * 2005-02-16 2007-12-11 Honeywell International , Inc. Axial loading management in turbomachinery
CN101922473A (zh) * 2010-03-24 2010-12-22 南通大通宝富风机有限公司 循环流化床风机
WO2011128587A1 (fr) 2010-04-14 2011-10-20 Turbomeca Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre
EP3557024A1 (de) * 2010-12-29 2019-10-23 Garrett Transportation I Inc. Turbolader mit integriertem aktuator

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040170181A1 (en) * 2003-02-27 2004-09-02 Padcom, Inc. Prioritized alternate port routing
US8935926B2 (en) 2010-10-28 2015-01-20 United Technologies Corporation Centrifugal compressor with bleed flow splitter for a gas turbine engine
CN103016363B (zh) * 2011-09-26 2016-01-20 珠海格力电器股份有限公司 一种离心压缩机及其控制方法
FR2981131B1 (fr) * 2011-10-07 2013-11-01 Turbomeca Compresseur centrifuge equipe d'un marqueur de mesure d'usure et procede de suivi d'usure utilisant ce marqueur
CN103062077B (zh) * 2011-10-24 2014-05-07 珠海格力电器股份有限公司 多级制冷压缩机及其中间补气结构
CN103206389B (zh) * 2012-01-12 2015-10-14 珠海格力电器股份有限公司 多级制冷压缩机及其中间补气结构
JP6294391B2 (ja) * 2016-06-28 2018-03-14 本田技研工業株式会社 コンプレッサ及び内燃機関の過給システム
US10677078B2 (en) 2017-05-25 2020-06-09 Pratt & Whitney Canada Corp. Gas turbine with a radial-to-axial intake, variable-angle inlet guide vane therefore, and method of operation
CN112983648B (zh) * 2021-04-13 2022-04-01 浙江大学 一种燃气轮机径向进气室流动主动控制装置
US11965459B2 (en) * 2022-04-18 2024-04-23 Pratt & Whitney Canada Corp. Air intake plenum with struts

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE672432A (de) * 1964-11-18 1966-03-16
FR2139741A1 (de) * 1971-06-03 1973-01-12 Snecma
FR2294345A1 (fr) * 1974-12-13 1976-07-09 United Turbine Ab & Co Compresseur a au moins deux etages
FR2438156A1 (fr) * 1978-10-05 1980-04-30 Alsthom Atlantique Grille d'aubes pour turbine ou compresseur
DE3717590A1 (de) * 1986-06-02 1987-12-03 Teledyne Ind Kompressor

Family Cites Families (11)

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FR672432A (fr) * 1929-04-03 1929-12-27 Mécanisme d'appareil de water-closet
US2962258A (en) * 1958-03-31 1960-11-29 Marquardt Corp Slotted vane turbine governor
DE2633480B2 (de) * 1976-07-26 1979-04-05 Aktiengesellschaft Kuehnle, Kopp & Kausch, 6710 Frankenthal Vorleitapparat für einen Ventilator großen Laufrad-Durchmessers
JPS572499A (en) * 1980-06-06 1982-01-07 Nissan Motor Co Ltd Tarbo compressor
US4436481A (en) * 1981-06-15 1984-03-13 The Garrett Corporation Intake vortex whistle silencing apparatus and methods
US4531356A (en) * 1981-06-15 1985-07-30 The Garrett Corporation Intake vortex whistle silencing apparatus and methods
US4643639A (en) * 1984-12-24 1987-02-17 Sundstrand Corporation Adjustable centrifugal pump
EP0212834B1 (de) * 1985-07-17 1990-11-14 Geoffrey Light Wilde Variabler Einlass für eine Radialturbine
JPS6418880U (de) * 1987-02-09 1989-01-30
JPH01227823A (ja) * 1988-03-08 1989-09-12 Honda Motor Co Ltd タービンの可変ノズル構造
JPH0759881B2 (ja) * 1988-04-15 1995-06-28 本田技研工業株式会社 可変容量タービン

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE672432A (de) * 1964-11-18 1966-03-16
FR2139741A1 (de) * 1971-06-03 1973-01-12 Snecma
FR2294345A1 (fr) * 1974-12-13 1976-07-09 United Turbine Ab & Co Compresseur a au moins deux etages
FR2438156A1 (fr) * 1978-10-05 1980-04-30 Alsthom Atlantique Grille d'aubes pour turbine ou compresseur
DE3717590A1 (de) * 1986-06-02 1987-12-03 Teledyne Ind Kompressor

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0719944A2 (de) * 1994-12-28 1996-07-03 Ebara Corporation Turbomaschine mit Strömungsleiteinrichtungen mit variablem Winkel
EP0719944A3 (de) * 1994-12-28 1998-06-10 Ebara Corporation Turbomaschine mit Strömungsleiteinrichtungen mit variablem Winkel
US5927939A (en) * 1994-12-28 1999-07-27 Ebara Corporation Turbomachine having variable angle flow guiding device
US7305826B2 (en) * 2005-02-16 2007-12-11 Honeywell International , Inc. Axial loading management in turbomachinery
CN101922473A (zh) * 2010-03-24 2010-12-22 南通大通宝富风机有限公司 循环流化床风机
WO2011128587A1 (fr) 2010-04-14 2011-10-20 Turbomeca Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre
EP3557024A1 (de) * 2010-12-29 2019-10-23 Garrett Transportation I Inc. Turbolader mit integriertem aktuator

Also Published As

Publication number Publication date
FR2696210B1 (fr) 1994-10-28
DE69318242T2 (de) 1998-12-24
US5484261A (en) 1996-01-16
JPH06317183A (ja) 1994-11-15
DE589745T1 (de) 1994-09-22
FR2696210A1 (fr) 1994-04-01
CA2106270A1 (fr) 1994-03-26
CA2106270C (fr) 1996-11-26
DE69318242D1 (de) 1998-06-04
JP2728356B2 (ja) 1998-03-18
EP0589745B1 (de) 1998-04-29

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