EP0589745B1 - Einlassregelanlage einer Turbomaschine - Google Patents

Einlassregelanlage einer Turbomaschine Download PDF

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Publication number
EP0589745B1
EP0589745B1 EP93402171A EP93402171A EP0589745B1 EP 0589745 B1 EP0589745 B1 EP 0589745B1 EP 93402171 A EP93402171 A EP 93402171A EP 93402171 A EP93402171 A EP 93402171A EP 0589745 B1 EP0589745 B1 EP 0589745B1
Authority
EP
European Patent Office
Prior art keywords
vane
compressor
control system
vanes
turbomachine
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 - Lifetime
Application number
EP93402171A
Other languages
English (en)
French (fr)
Other versions
EP0589745A1 (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 setting the air supply conditions of a turbomachine.
  • the invention relates in particular to a system of setting for a compressor air intake system centrifugal, and more particularly of the centrifugal compressor external from 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 the compressors, and which allows these suction machines directly, or through a plenum, ambient air to properly feed their part axial input.
  • means for adjusting the supply conditions of the tubomachine such as guide vanes, are arranged around the axis of the machine and at intervals regular on a given diameter.
  • These blades are generally with variable angular setting and they can be rotated simultaneously between two extreme positions.
  • the adjustment system allows to reduce significantly the flow through the compressor and therefore the power needed to train it.
  • Such an adaptation is necessary during the phases of starting certain rotary compressor machines external or auxiliary.
  • control means and the cylinder actuation then have a complex structure and expensive.
  • the blades are in the fully closed position, or almost complete, and it is necessary to disassemble in parts the air intake device to perform a endoscopic inspection of certain organs of the auxiliary power, and for example blades of the compressor. This inspection also requires 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 a system for setting of the type mentioned above which allows simultaneously remedy the disadvantages that come to be mentioned.
  • the system of the invention allows the adjustment of the air supply conditions of a turbomachine of the type comprising a series of guide vanes mounted movable between an open position and a closed position of a pipe air inlet of the turbomachine. At least one of the guide vanes has an orifice opening onto the profiled body of the blade. Said blades are arranged in a crown, and each blade is pivotally mounted around an axis parallel to the axis of the crown.
  • said opening orifice crosses the body of the blade and is arranged under the shape of a slit extending in the middle part of the blade substantially in the longitudinal direction of the gas flow the along the dawn, so as to connect the lower surface and the dawn surface and to create a secondary air flow capable of avoiding excessive heating of the turbomachine compressor and allowing endoscopic inspection of the blades.
  • 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 gas turbine, characterized in that it comprises a compressor external centrifugal load with which the air intake system is fitted an adjustment system produced in accordance with the teachings of the invention.
  • FIG. 1 represents a diagram of an auxiliary group of gas turbine power with an external compressor of load can be fitted 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 of a system according to the invention.
  • Figure 3 is a half sectional view of a charge compressor air inlet line shown in Figure 2.
  • Figure 4 is a half cross-sectional view of the annular line of the charge compressor, according to the line 4-4 of figure 3, and in which the blades are shown in the open position complete.
  • 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 the corresponding intermediate position to a gyratory flow downstream of these.
  • Figure 7 is a perspective view of a blade director with a port for communication of its upper surface with its lower surface, corresponding to a mode for carrying out the invention.
  • the adjustment system according to the invention finds in particular to apply in the case of auxiliary groups gas turbine power, as will be described more in detail later, 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 that turboshaft engines, turbopropellers, turbochargers, auxiliary power units to direct debit, etc.
  • this compressor can be of the type axial, radial or mixed.
  • 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 turbine to gas, comprising a charge compressor fitted with a adjustment system according to the invention.
  • this set designated by the general reference 1 comprises a turbine engine 2 shown diagrammatically in the area bounded by a dashed line outline.
  • 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 other devices operated by compressed air such as than pneumatic turbine engines or the like.
  • an accessory pneumatic assembly such as for example an air conditioning system 4 of an airplane or other devices operated by compressed air such as than pneumatic turbine engines or the like.
  • Turboshaft 2 is also suitable for drive an electric generator 5.
  • a drive shaft 6 which comprises by example a conventional type reducer (not shown).
  • the burnt gases 11 are expanded in a turbine two-stage axial 12 to provide the desired power to the drive shaft 6, before being ejected into the atmosphere through an exhaust nozzle 13 arranged downstream of the turbine.
  • the rotation of the shaft 6 ensures the training of power compressor 8, charge compressor 3, the electric generator 5 and possibly others accessories.
  • the compressor has an annular air inlet pipe 14 allowing air to be drawn into a plenum 15 and to power a centrifugal mobile 16.
  • the centrifugal mobile 16 has a series blades 17 for transforming into pneumatic energy mechanical energy transmitted by the drive shaft 6.
  • Air leaks at the top of mobile vanes 17 are limited by a static cover 18.
  • the charge compressor also has a diffusion assembly consisting of a diffuser 19, a radial vane diffuser 20 and a volute 21 which is intended to supply compressed air to the pneumatic assembly 4 mentioned previously.
  • the radial air flow is then transformed in axial flow to properly power the mobile centrifugal 16.
  • the air 22 is compressed by the blades 17 in rotation and is pushed tangentially across broadcast.
  • the kinetic energy of the air leaving the mobile 16 is then transformed into pressure in the diffuser smooth 19 and in the radial vane diffuser 20.
  • Means for adjusting feeding conditions are also provided to adjust the air flow and pressure level supplied to the assembly pneumatic 4.
  • These means consist of a system of setting designated by the general reference 23 in the figure 2, which comprises a series of guide vanes 24 arranged in the radial part of the annular inlet pipe air 14.
  • the vanes 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 pitch and are simultaneously orientable through control shafts 26 and a mechanical assembly control aid 28.
  • the adjustment system significantly reduces air flow passing through the compressor and thereby the necessary power to train him through the tree 6 of the turbine engine 2.
  • heating may occur excessive downstream of guide vanes 24 which is detrimental the mechanical strength of the entire compressor, and in particular to the holding of the centrifugal mobile 16, of the diffuser radial 20 and / or volute 21.
  • At least one blade 24 has an orifice 27 for sound communication upper surface with its lower surface.
  • the orifice 27 can be made in the form of a through slot longitudinal, that is to say which extends in the part median of directing dawn 24 substantially according to the longitudinal direction of gas flow along dawn.
  • Ports 27 for communication can be arranged in all of the guide vanes, in a single blade, in two diametrically opposite blades, in three blades arranged at 120 ° relative to the others, or in any other configuration of blades.
  • the holes are inoperative because the small pressure difference between the intrados and extrados of guide vanes.
  • the adjustment system according to the invention is particularly simple to carry out since it requires no additional mechanical parts and also allows a slight reduction in the mass of the system.
  • the endoscopic inspection is very simple, in the fully closed position, by inserting the endoscope through an orifice 27.
  • flow gyratory imposed on the gas flow downstream of the blades guidelines 24 may cause unwanted aerodynamic noise due to noise disturbance caused to the environment immediate, due to the corresponding energy loss inside the annular pipe and because of the risks of vibratory excitation of mechanical parts arranged 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)

Claims (7)

  1. Anlage (23) zur Regelung der Lufteinlaßbedingungen einer Turbomaschine umfassend eine Reihe von Leitschaufeln (24), welche verstellbar zwischen einer Öffnungs- und einer Schließposition einer Lufteinlaßleitung (14) der Turbomaschine montiert sind, in welcher wenigstens eine der Leitschaufeln (24) eine Durchflußöffnung (27) umfaßt, welche den Profilkörper der Schaufel durchdringt, wobei die Schaufeln (24) kronenförmig angeordnet sind, und jede Schaufel um eine zur Kronenachse parallele Achse (26) drehbar gelagert ist,
    dadurch gekennzeichnet,
    daß die Durchflußöffnung (27) den Körper der Schaufel durchdringt und als Schlitz ausgebildet ist, welcher sich in dem mittleren Bereich der Schaufel (24) im wesentlichen in Längsrichtung des Gasflusses entlang der Schaufel erstreckt, so daß die Unterseite und die Oberseite der Schaufel (24) in Verbindung miteinander gebracht und ein sekundärer Luftfluß erzeugt wird, um eine übermäßige Erwärmung des Kompressors der Turbomaschine zu vermeiden und eine endoskopische Inspektion der Beschaufelung zu ermöglichen.
  2. Regelanlage gemäß Anspruch 1,
    dadurch gekennzeichnet,
    daß eine Durchflußöffnung (27) in einer einzigen Leitschaufel (24) angebracht ist, um den von Vibrationserscheinungen verursachten aerodynamischen Lärm zu verringern.
  3. Regelanlage gemäß Anspruch 1,
    dadurch gekennzeichnet,
    daß Durchflußöffnungen (27) in zwei diametral entgegengesetzten Leitschaufeln (24) angebracht sind, um den von Vibrationserscheinungen verursachten aerodynamischen Lärm zu verringern.
  4. Regelanlage gemäß Anspruch 1,
    dadurch gekennzeichnet,
    daß Durchflußöffnungen (27) in drei um 120° bezüglich einander angeordneten Leitschaufeln (24) angebracht sind, um den von Vibrationserscheinungen verursachten aerodynamischen Lärm zu verringern.
  5. Regelanlage gemäß Anspruch 1,
    dadurch gekennzeichnet,
    daß in der Schließstellung die Hinterkante und die Vorderkante zweier aufeinanderfolgenden Schaufeln (24) jeweils aneinander anliegen sind, da die Schaufeln (24) aneinanderstoßen.
  6. Zentrifugalkompressor,
    dadurch gekennzeichnet,
    daß er ein Luftzufuhrsystem umfaßt, welches mit einer Regelanlage gemäß einem der vorangegangenen Ansprüche versehen ist.
  7. Hilfsleistungsgruppe für eine Gasturbine,
    dadurch gekennzeichnet,
    daß sie einen externen Zentrifugalladekompressor gemäß Anspruch 6 umfaßt.
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 EP0589745A1 (de) 1994-03-30
EP0589745B1 true 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)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0719944B1 (de) * 1994-12-28 2002-05-29 Ebara Corporation Turbomaschine mit Strömungsleiteinrichtungen mit variablem Winkel
US20040170181A1 (en) * 2003-02-27 2004-09-02 Padcom, Inc. Prioritized alternate port routing
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
FR2958967B1 (fr) 2010-04-14 2013-03-15 Turbomeca Procede d'adaptation de debit d'air de turbomachine a compresseur centrifuge et diffuseur de mise en oeuvre
US8935926B2 (en) 2010-10-28 2015-01-20 United Technologies Corporation Centrifugal compressor with bleed flow splitter for a gas turbine engine
US8641363B2 (en) * 2010-12-29 2014-02-04 Honeywell International Inc. Turbocharger with integrated actuator
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

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Also Published As

Publication number Publication date
FR2696210B1 (fr) 1994-10-28
EP0589745A1 (de) 1994-03-30
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

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