EP2268925B1 - Compresseur de turbine à gaz - Google Patents
Compresseur de turbine à gaz Download PDFInfo
- Publication number
- EP2268925B1 EP2268925B1 EP09727042.5A EP09727042A EP2268925B1 EP 2268925 B1 EP2268925 B1 EP 2268925B1 EP 09727042 A EP09727042 A EP 09727042A EP 2268925 B1 EP2268925 B1 EP 2268925B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- valves
- gas turbine
- blow
- openings
- 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.)
- Not-in-force
Links
Images
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 ports for stabilizing the compressor flow and a plurality of valves for controlling the amount of air blown through the injection ports, wherein a plurality of coupled with the control of the valves sensors distributed in the region of the blades on the circumference of the flow channel are.
- 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.
- Solutions in the prior art are, in particular, the injection of air into the housing or rotor region of a compressor under certain operating conditions. By this lateral injection of air in the direction of blades to the flow in the compressor be stabilized.
- the injection of air can be stationary (without changing the Einblasmassenstroms) or controlled by means of valves, the latter in the DE 10 2005 052 466 A1 and the US 6,125,626 is described.
- the document US-A-5 340 271 relates to a gas turbine compressor with valve-controlled injection ports for stabilizing the compressor flow.
- the control of the valves is coupled to sensors in the region of the blades, wherein a plurality of sensors are arranged distributed on the circumference of the flow channel.
- the sensors are designed as a flow rate detecting hot wire sensors.
- the document refers to a state of the art in which pressures are converted into control signals.
- the object of the invention in contrast, is to make the stabilization of the flow by blowing in the area of the blades even more effective and precise.
- the gas turbine compressor according to the invention of the aforementioned type provides that a plurality of pressure sensors distributed on the circumference of the flow channel are arranged upstream and downstream of the injection openings.
- a plurality of pressure sensors distributed on the circumference of the flow channel upstream and downstream of the injection openings the pressures can be determined before and after introduction of the additional air, which is even more effective and permits even more precise regulation or control.
- 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 electrical control coupled to a plurality of valves provided at the periphery of the flow passage at inflow ports.
- 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 is a multi-stage gas turbine compressor shown in axial design.
- the gas turbine compressor has an annular compressor housing 2, arranged on the housing 2 vanes 4 and a plurality 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 blade ring 8, the housing 2 has outlet openings 12, are discharged via the compressed air from the annular channel 14 and, as shown by the arrow, is guided to the injection openings 10.
- the air injected to stabilize the compressor flow is directed directly at the blade tip, such as FIG. 1 shows.
- valves 16 connected to a controller 18 (see FIG. FIG. 2 ) are controlled.
- the valves 16 are so-called microvalves, which in FIG. 4 are shown. 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.
- FIG. 3 It can be seen that 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 FIG. 2 ).
- microvalves one of which in FIG. 4 can be seen in 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)
Claims (6)
- Compresseur de turbine à gaz, avec un corps de compresseur (2), des aubes directrices (4), des aubes mobiles (8), des orifices d'admission d'air commandés par soupape (10) pour stabiliser l'écoulement du compresseur et plusieurs soupapes (16) pour la commande du débit d'air insufflé par les orifices d'admission d'air (10), dans lequel plusieurs capteurs (20, 22) couplés avec la commande (18) des soupapes (16) sont disposés dans la région des aubes mobiles (8) en étant répartis à la périphérie du canal d'écoulement (14), caractérisé en ce que les capteurs sont des capteurs de pression (20, 22) et sont disposés en amont et en aval des orifices d'admission d'air (10).
- Compresseur de turbine à gaz selon la revendication 1, caractérisé en ce que les orifices d'admission d'air (10) sont disposés immédiatement en amont des aubes mobiles (8) parcourues en plus par de l'air.
- Compresseur de turbine à gaz selon la revendication 1 ou 2, caractérisé en ce qu'une soupape particulière (16) est associée à chaque orifice d'admission d'air (10).
- Compresseur de turbine à gaz selon l'une quelconque des revendications précédentes, caractérisé en ce que les soupapes (16) sont des micro-soupapes.
- Procédé pour stabiliser l'écoulement de compresseur de turbine à gaz d'un compresseur de turbine à gaz selon la revendication 1 au moyen d'une commande électrique (18), qui est couplée aux soupapes (16) disposées à la périphérie du canal d'écoulement (14) aux orifices d'admission d'air (10), caractérisé en ce que l'on détermine les rapports de pression dans le canal d'écoulement (14) et on commande les soupapes (16) en fonction de ceux-ci, et en ce que l'on détecte les rapports de pression en amont et en aval des orifices d'admission d'air (10).
- Procédé selon la revendication 5, caractérisé en ce que l'on ouvre les soupapes (16) au choix de façon continue, modulée ou pulsée.
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 EP2268925A1 (fr) | 2011-01-05 |
EP2268925B1 true 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)
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)
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 |
US6517309B1 (en) * | 1998-03-13 | 2003-02-11 | Unitec Institute Of Technology | Pumping apparatus and methods |
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 |
-
2008
- 2008-04-02 DE DE102008016800A patent/DE102008016800A1/de not_active Withdrawn
-
2009
- 2009-04-02 CA CA2720172A patent/CA2720172A1/fr not_active Abandoned
- 2009-04-02 WO PCT/DE2009/000461 patent/WO2009121350A1/fr active Application Filing
- 2009-04-02 US US12/935,850 patent/US8628291B2/en not_active Expired - Fee Related
- 2009-04-02 EP EP09727042.5A patent/EP2268925B1/fr not_active Not-in-force
Also Published As
Publication number | Publication date |
---|---|
WO2009121350A1 (fr) | 2009-10-08 |
CA2720172A1 (fr) | 2009-10-08 |
US8628291B2 (en) | 2014-01-14 |
US20110103931A1 (en) | 2011-05-05 |
DE102008016800A1 (de) | 2009-10-08 |
EP2268925A1 (fr) | 2011-01-05 |
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