EP2268925A1 - Compresseur de turbine à gaz - Google Patents

Compresseur de turbine à gaz

Info

Publication number
EP2268925A1
EP2268925A1 EP09727042A EP09727042A EP2268925A1 EP 2268925 A1 EP2268925 A1 EP 2268925A1 EP 09727042 A EP09727042 A EP 09727042A EP 09727042 A EP09727042 A EP 09727042A EP 2268925 A1 EP2268925 A1 EP 2268925A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
valve
compressor
valves
turbine compressor
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
EP09727042A
Other languages
German (de)
English (en)
Other versions
EP2268925B1 (fr
Inventor
Sven-J. Hiller
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2268925A1 publication Critical patent/EP2268925A1/fr
Application granted granted Critical
Publication of EP2268925B1 publication Critical patent/EP2268925B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F04D27/0238—Details or means for fluid reinjection
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection

Definitions

  • the invention relates to a gas turbine compressor with a compressor housing, guide vanes, blades, valve-controlled injection openings for stabilizing the compressor flow and at least one valve for controlling the amount of air injected via the injection openings.
  • Compressors may start pumping under certain operating conditions (throttle condition). Typically, the pumping results from an unstable flow condition. This condition can preferably occur in the partial load range (off-design state).
  • the compressor of gas turbines is designed for certain flight conditions in which it must provide the pre-calculated characteristics such as throughput, pressure ratio, efficiency, etc. But even beyond these design points, the compressor still has acceptable and safe operating characteristics, e.g. in the landing approach of an aircraft, where fast thrust changes and thus fast speed changes are required for adherence to a glide path. But even when starting in the lower speed range of the compressor to ensure proper flow and must allow a quick start up to full load.
  • the compressor map is also measured in the partial load range.
  • the so-called driving line the operating points on different speed lines interconnected, have a sufficient safety margin to the so-called surge limit, in which, as I said, a stall takes place on the compressor blades.
  • the injection of air can be stationary (without changing the Einblasmassenstroms) or controlled by means of valves, the latter being described in DE 10 2005 052 466 Al and US 6,125,626.
  • the object of the invention is to further improve the stabilization of the flow in the region of the rotor blades.
  • the inventive gas turbine compressor of the aforementioned type provides that at least one pressure sensor coupled to the control of the valve is provided in the region of the rotor blades for detecting the pressure in the compressor, the valve being controllable in dependence on the determined pressure.
  • the invention provides, via pressure sensors in the decisive areas, namely in the area of the rotor blades, to detect the actual prevailing pressure and, as it were, depends on the practical and non-theoretical actual value to control the air supply.
  • a plurality of pressure sensors distributed on the circumference of the flow channel are provided. These pressure sensors are, so to speak, on a kind of ring.
  • even more pressure sensors distributed around the circumference of the flow channel are provided upstream and downstream of the injection ports, so that the pressures can be determined before and after introduction of the additional air, which is even more effective.
  • the injection ports should be located immediately upstream of the blades.
  • injection ports may also have one of numerous valves, to save components and costs.
  • valves assigned to the injection openings allow continuous, modulated or pulsed flows to be achieved.
  • Modular peripheral disorders can be eradicated by targeted anti-phase injection as in the case of anti-sounding.
  • peak-like disturbances can be effectively remedied by a quick, complete opening of one or more valves.
  • valve or valves are microvalves, in particular based on MEMS technology.
  • Such valves are characterized by a fast switchability and usually have an external actuator, which can also modulate / oscillate the valve (for example, with 400 Hz).
  • the control of the pressure sensors can be integrated in the respective pressure sensor itself, so that a pressure sensor is assigned to one or more valves and controls them directly, or a central control can be provided.
  • the actuators are in particular magnetic coils or piezo elements.
  • valves and the injection openings are located in particular in the outer housing, but also an inflow in the hub area is alternatively possible.
  • the invention further provides a method for stabilizing the gas turbine compressor flow by means of an electric control, which is coupled to a plurality of valves provided at the circumference of the flow channel at inflow openings.
  • the inventive method provides that the pressure conditions determined in the flow channel and depending on the valves are controlled. This determination is made directly via the pressure sensors.
  • the pressure conditions are detected in particular upstream and / or downstream of the inlet openings.
  • valves can optionally be continuous, modulated or pulsed open, the control allows for all these possibilities.
  • FIG. 1 shows a longitudinal sectional view through a gas turbine compressor according to the invention
  • FIG. 2 shows a detailed view of the compressor according to the invention in the region of a rotor blade, wherein guide vanes have been omitted for clarity;
  • FIG. 3 shows a perspective top view of a part of the compressor housing
  • Figure 4 is an enlarged view in the range of a microvalve, which is used in the compressor according to the invention.
  • FIG. 1 shows a multi-stage gas turbine compressor of axial design.
  • the gas turbine compressor has an annular compressor housing 2, arranged on the housing 2 vanes 4 and a plurality of arranged on a rotor 6 blades 8.
  • the housing 2 Immediately upstream of the blade tip of a blade ring, the housing 2 on the circumference evenly distributed injection openings 10 on. Downstream of this rotor blade ring 8, the housing 2 has outlet openings 12, via which compressed air is discharged from the annular channel 14 and, as represented by the arrow, is led to the injection openings 10.
  • the air injected to stabilize the compressor flow is directed directly at the blade tip, as shown in FIG.
  • valves 16 coupled to a controller 18 (see Figure 2).
  • the valves 16 are so-called microvalves, which are shown in FIG. These microvalves have dimensions of just about 10 x 15 mm surface and a thickness of about 1 mm and are particularly well to be placed on the outer housing 2 to save space.
  • Each injection port 10 has its own valve 16 associated therewith.
  • valve 16 there is a kind of ring of valves 16 which extend around the housing 2 and are fixed directly to the housing 2.
  • pressure sensors 20, 22 are mounted on the housing 2, which determine the pressure before, in the area or after the flown blades 8 (see Figure 2).
  • microvalves in more detail, one of which can be seen in FIG. 4 in a greatly enlarged representation.
  • the actuator may be, for example, a small-sized magnetic coil 24 including plunger 26 or a piezo actuator.
  • the supply line 28 is shown for the branched air.
  • microvalves are attached to the housing 2, correspondingly many injection openings 10 are provided.
  • injection openings 10 are provided.
  • blade rings can be provided with its own ring of injection openings 10.
  • valves 20, 22 are closed via the control 18 or individual or all valves 20, 22 are opened simultaneously or successively.
  • Each valve 20, 22 is individually controlled so that synchronized control of all the valves 20, 22 is possible to produce any circumferential waveforms or circulating waves of injected air.
  • These circumferential shafts can compensate for circumferential disturbances of the compressor flow, as the compressors can often exhibit modal flow disturbances in certain operating conditions that can be damped or completely extinguished by the targeted antiphase injection.
  • the targeted opening, closing or modulating the incoming air quantity for beam generation can be compared to a steady, steady inflow of branched air significantly reduced.
  • the controller 18 may also be integrated in the microvalves 16.
  • valves 16 are closed again so as not to unnecessarily reduce the efficiency.

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)
  • Control Of Positive-Displacement Air Blowers (AREA)

Abstract

L'invention concerne un compresseur de turbine à gaz muni d'un carter de compresseur (2), d'aubes directrices (4), ainsi que d'aubes mobiles (8). Le compresseur selon l'invention présente des ouvertures d'insufflation (10) commandées par soupape et servant à stabiliser l'écoulement du compresseur au moyen d'air insufflé. L'écoulement d'air est détecté au moyen de capteurs de pression (20, 22), les soupapes (16) étant commandées en fonction de la pression déterminée.
EP09727042.5A 2008-04-02 2009-04-02 Compresseur de turbine à gaz Not-in-force EP2268925B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008016800A DE102008016800A1 (de) 2008-04-02 2008-04-02 Gasturbinenverdichter
PCT/DE2009/000461 WO2009121350A1 (fr) 2008-04-02 2009-04-02 Compresseur de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2268925A1 true EP2268925A1 (fr) 2011-01-05
EP2268925B1 EP2268925B1 (fr) 2015-01-21

Family

ID=40853880

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09727042.5A Not-in-force EP2268925B1 (fr) 2008-04-02 2009-04-02 Compresseur de turbine à gaz

Country Status (5)

Country Link
US (1) US8628291B2 (fr)
EP (1) EP2268925B1 (fr)
CA (1) CA2720172A1 (fr)
DE (1) DE102008016800A1 (fr)
WO (1) WO2009121350A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009032549A1 (de) * 2009-07-10 2011-01-13 Mtu Aero Engines Gmbh Verfahren zum Mindern von Schwingungsamplituden
DE102011107523B4 (de) * 2011-07-15 2016-08-11 MTU Aero Engines AG System zum Einblasen eines Fluids, Verdichter sowie Turbomaschine
CN105673532B (zh) * 2016-01-28 2019-02-05 江苏大学 一种消除轴流风机小流量运行不稳定装置
US10876549B2 (en) 2019-04-05 2020-12-29 Pratt & Whitney Canada Corp. Tandem stators with flow recirculation conduit

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4196472A (en) * 1977-09-09 1980-04-01 Calspan Corporation Stall control apparatus for axial flow compressors
US5275528A (en) * 1990-08-28 1994-01-04 Rolls-Royce Plc Flow control method and means
US5340271A (en) * 1990-08-18 1994-08-23 Rolls-Royce Plc Flow control method and means
US6059522A (en) * 1996-04-17 2000-05-09 United Technologies Corporation Compressor stall diagnostics and avoidance
US6055805A (en) * 1997-08-29 2000-05-02 United Technologies Corporation Active rotor stage vibration control
BR9909246A (pt) * 1998-03-13 2000-11-28 Unitec Inst Of Technology Aparelhos e métodos de bombeamento aperfeiçoados
US7003426B2 (en) * 2002-10-04 2006-02-21 General Electric Company Method and system for detecting precursors to compressor stall and surge
DE102005052466A1 (de) 2005-11-03 2007-05-10 Mtu Aero Engines Gmbh Mehrstufiger Verdichter für eine Gasturbine mit Abblasöffnungen und Einblasöffnungen zum Stabilisieren der Verdichterströmung

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009121350A1 *

Also Published As

Publication number Publication date
DE102008016800A1 (de) 2009-10-08
WO2009121350A1 (fr) 2009-10-08
CA2720172A1 (fr) 2009-10-08
US20110103931A1 (en) 2011-05-05
EP2268925B1 (fr) 2015-01-21
US8628291B2 (en) 2014-01-14

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