EP0638727A1 - Compresseur ainsi que sa méthode de fonctionnement - Google Patents

Compresseur ainsi que sa méthode de fonctionnement Download PDF

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Publication number
EP0638727A1
EP0638727A1 EP94111521A EP94111521A EP0638727A1 EP 0638727 A1 EP0638727 A1 EP 0638727A1 EP 94111521 A EP94111521 A EP 94111521A EP 94111521 A EP94111521 A EP 94111521A EP 0638727 A1 EP0638727 A1 EP 0638727A1
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EP
European Patent Office
Prior art keywords
compressor
heating
compressed air
housing
channels
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
EP94111521A
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German (de)
English (en)
Other versions
EP0638727B1 (fr
Inventor
Pierre Meylan
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.)
ABB AG Germany
Original Assignee
ABB Management AG
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 ABB Management AG filed Critical ABB Management AG
Publication of EP0638727A1 publication Critical patent/EP0638727A1/fr
Application granted granted Critical
Publication of EP0638727B1 publication Critical patent/EP0638727B1/fr
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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components

Definitions

  • the present invention relates to the field of turbomachines. It relates to a compressor, in particular for a gas turbine, which compressor comprises a rotor which has a plurality of rotor blades on its circumference and is rotatably mounted about a compressor axis, and a compressor housing which concentrically surrounds the rotor, between the outer ends of the rotor blades and the A radial clearance is provided on the inner wall of the compressor housing.
  • the invention further relates to a method for operating such a compressor.
  • a compressor of the type mentioned is e.g. known from the document DE-A1-39 09 606.
  • rings of rotor blades are arranged one behind the other in several pressure stages on a rotor shaft and are concentrically surrounded by a compressor housing.
  • a radial clearance of the order of magnitude of 1 mm is provided between the outer ends of the rotor blades and the inner wall of the compressor housing, which is kept as small as possible to keep the backflow of air and the associated reduction in efficiency low.
  • the reduction in radial play is made more difficult by the fact that in different operating states of the compressor, rotor blades and compressor housing expand or contract to different extents.
  • the radial clearance must therefore be selected so that it is still sufficient under the most unfavorable operating conditions, i.e. with the rotor and blades extended and the compressor housing contracted.
  • the change in the radial play can have both mechanical and thermal causes.
  • the radial deflection of the rotor and the rotor blades due to the centrifugal forces acting during fast rotation are the main mechanical causes.
  • Different thermal expansions in the rotor and stator due to temperature differences or different expansion coefficients of the materials used are to be regarded as thermal causes.
  • a temperature control of the compressor housing has already been proposed (US-A-4,230,436), in which the temperature of the compressor housing is lowered in a controlled manner by a more or less strong cooling air flow.
  • the cooling air is extracted from different compressor stages and guided in cooling channels both behind the guide vanes and behind the inner wall of the compressor housing opposite the rotor blades.
  • the known methods for active backlash control relate to the normal operation of the compressor. You can therefore also use compressor air of different temperatures or - in the case of a gas turbine compressor - hot gas from the engine part to cool or heat various compressor parts or parts.
  • the object is achieved in a compressor of the type mentioned at the outset in that, in order to reduce the fluctuations in the radial play, the compressor housing is designed to be heatable and is connected to a separate heating device which is independent of the operation of the compressor and by means of which it can be heated during a warm start.
  • the essence of the invention is to provide a heating device that works independently of the operation of the compressor and can heat the compressor housing before a warm start to such an extent that a reduction in the radial play due to a temperature gradient between the rotor and stator practically no longer occurs.
  • a first preferred embodiment of the compressor according to the invention is characterized in that a plurality of circumferential heating channels are provided in the compressor housing and are arranged one behind the other in the direction of the compressor axis, through which a heated heating medium can be sent all round that the compressor housing has a plurality on its inner circumference is occupied by guide vanes that for receiving the guide vanes are provided on the inner circumference of the compressor housing, in which the guide vanes are inserted with corresponding vane feet, and that the heating channels are each formed by grooves which are embedded in the bottoms of the vane rotations.
  • a second preferred embodiment of the invention is characterized in that several, preferably three, heating channels are connected in series in a row, that the heating medium flows through this row against the direction of flow of the compressor, that each heating channel per se forms a circular ring, and in the case of heating ducts connected in series, the adjacent individual heating ducts are interconnected by transfer ducts running parallel to the compressor axis. This enables effective and uniform heating with a minimized number of external connections.
  • compressed air is used as the heating medium
  • the heating device comprises a compressed air connection, from which a compressed air supply leads via a heater to the compressor housing, and the heater is designed as an electric heater (but can also be carried out by means of a gas burner).
  • the method according to the invention is characterized in that, in preparation for a warm start, the compressor housing is heated after the compressor has been switched off, and in that the heating is only ended when the compressor has a certain part, preferably about 75% to 100%, of its after the warm start Has reached full load. This ensures that external heating power is only supplied to the housing until the operating temperatures of the rotor and stator have equalized.
  • a preferred embodiment of the method according to the invention is characterized in that, for heating the compressor housing, compressed air is heated and pressed through heating channels running in the compressor housing, and in that when the compressor starts warm, compressed air is first supplied from outside and, after reaching a predetermined working pressure in the compressor, the supply of compressed air interrupted from the outside and in its place compressed air is diverted from the outlet of the compressor and used.
  • FIG. 1 a preferred embodiment of a compressor according to the invention is shown in longitudinal section along the rotor axis.
  • the compressor 1 comprises a rotor 3 and a compressor housing 2 concentrically surrounding the rotor 3.
  • a plurality of rotor blade rings which in turn each have a plurality of rotor blades 5a-d, are arranged one behind the other on the rotor 3 along the rotor axis.
  • the rotor blades are fastened to the rotor 3 with corresponding blade feet (the hatching due to the cutting has been omitted on the rotor for the sake of simplicity).
  • Each of the rotor blades forms its own compressor stage.
  • Guide vane rings are arranged between the individual rotor blade rings, the individual guide vanes 4a, b of which are fastened to the compressor housing 2 (as a blade carrier) with corresponding blade roots 6a, b (as the blade guide ring 8 is omitted for better visibility of the blade rotations 8).
  • a radial play is provided between the outer ends of the rotor blades 5a-d and the inside of the compressor housing 2 as well as between the inner ends of the guide blades 4a, b and the outer surface of the rotor 3, which is selected so that grinding is possible in every operating state of the blade ends on the opposite wall is reliably avoided, and on the other hand the efficiency of the compressor is not unnecessarily reduced by the gap which arises.
  • the medium to be compressed (for example the combustion air of a turbine) flows between the rotor 3 and the compressor housing 2 through the blade rings from right to left in the illustration, is compressed and heats up increasingly. Part of the resulting compression heat is given off to rotor 3, compressor housing 2 and blades 5a-d and 4a, b.
  • the present invention provides for the compressor housing to be heated up during a warm start in such a way that the excessive cooling is compensated for and therefore no need to be taken into account when selecting the radial play in the event of a warm start.
  • two heating channels 7a-c are provided in the compressor housing, through which a heated heating medium, in particular water vapor or compressed air, can be pressed all around under pressure.
  • a heated heating medium in particular water vapor or compressed air
  • the use of water vapor is particularly conceivable if (i) there is a vapor source, (ii) the temperature of the metal is less than 600 ° C, and (iii) the temperature of the water vapor is greater than that of the compressor air.
  • the heating channels 7a-c are simply designed as annular circumferential grooves in the bottoms of the blade rotations 8 and can thus be made in the same way when manufacturing the blade rotations 8.
  • the heating channels 7a-c are connected in series and the heating medium flows through them counter to the direction of flow of the compressor 1, that is to say from left to right in the illustration in FIGS. 1 to 3.
  • the series connection results in an axial temperature gradient, which corresponds approximately to the temperature gradient that arises in the compressor during operation.
  • the heating medium is preferably conducted in adjacent heating channels with a changing direction of rotation (see FIG. 6).
  • the series connection can in principle be realized by a suitable external connection between the individual adjacent heating channels. In the context of the invention, however, an internal series connection is preferred, which can be explained with reference to FIGS. 2 to 4 (a parallel connection is also conceivable, depending on the pressure difference ⁇ p).
  • the preferred internal series connection of the heating channels 7a-c takes advantage of the fact that the compressor housing 2 is generally divided into two halves along a parting plane 18, an upper housing part 2b and a lower housing part 2a (FIG. 4). From the parting plane 18, transfer channels 9, 16 are alternately milled into the upper housing part 2b and the lower housing part 2a, the two adjacent heating channels (in FIG. 2, the heating channels 7a and 7b, and in FIG. 3, the heating channels 7b and 7c) ) connect with each other. With three heating channels 7a-c connected in series, a total of two transfer channels (9 and 16) are necessary.
  • FIG. 2 shows the section through the upper housing part 2b along the plane ZZ from FIG. 4; the transfer channel 9 is cut accordingly.
  • Fig. 3 shows the top view of the Lower housing part 2a from the parting plane 18; the transfer channel 16 can be seen accordingly in the top view.
  • the transfer channel 9 (as well as the transfer channel 16) is closed off towards the parting plane 18 by a partition plate 17 (FIG. 4).
  • the separating plate 17 is wider and longer than the associated transfer channel and rests on a shoulder surrounding the channel (10 for the transfer channel 9 in FIG. 2 and 15 for the transfer channel 16 in FIG. 3).
  • the separating plate 17 extends to the compressor axis up to the blade rotations 8 and thereby simultaneously interrupts the two heating channels 7 a, b in the separating plane 18, which are connected by the associated transfer channel 9. This interruption is necessary in order to be able to determine a specific flow direction of the heating medium in the respective heating channel.
  • Both transfer channels 9, 16 overlap in the area of the central heating channel 7b, but are separated from one another there by the two separating plates.
  • the heating medium is now fed through an inlet channel 14 and an inlet space 13 (FIG. 2) into the most downstream heating channel 7a.
  • the inlet duct 14 opens into the heating duct on the side of the separating plate 17 opposite the transfer duct 9 (FIG. 4).
  • the heating medium circles the compressor axis once in a first direction of rotation in the first heating channel 7a, then passes through the first transfer channel 9 into the central heating channel 7b, circles the compressor axis a second time there in an opposite direction of rotation, then reaches the second axis via the second transfer channel 16 third heating duct 7c, circles the compressor axis there a third time in a new direction of rotation and finally exits again via an outlet space 11 and outlet duct 12 (FIGS. 2 and 6) connected to the heating duct 7c.
  • This flow path of the heating medium through the three heating channels 7a-c connected in series by means of the transfer channels 9, 16 is once again for clarification in a schematic perspective illustration reproduced in Fig. 6.
  • the heating channels are each connected in series in groups of three channels, it goes without saying that the interconnection of different heating channels can also be carried out in a different manner within the scope of the invention.
  • Compressed air, especially clean instrument air, is preferred as the heating medium. 5
  • the compressed air is transported to the compressor housing 2 via a compressed air connection 25 and a heater 22 by means of a compressed air supply line 27.
  • the heater 22 is preferably a gas-operated heat exchanger (propane, butane or the like) or an electrical (resistance) heater.
  • the compressed air with a pressure of about 0.6 MPa is heated in the heater 22 and pressed into the heating channels 26 as soon as the compressor 1 is switched off.
  • the temperature of the pressure medium reached with the heater 22 is preferably selected 50 to 100 K above the metal temperature of the compressor during normal operation (i.e. about 600 ° C).
  • the heating and the compressed air supply are switched off as soon as the compressor has reached a certain part of its full load, preferably approximately 75% to 100%.
  • This can be done via a main valve 24, which is arranged between compressed air connection 25 and heater 23.
  • an auxiliary line 19 can additionally open into the compressed air supply line 27, which contains a check valve 21 and can be supplied with compressor air.
  • the compressor air then takes the place of the compressed air supplied from the outside when the compressor itself generates sufficient pressure after starting to open the check valve 21.
  • a valve 28 is additionally provided in the auxiliary line 19, which valve is closed in normal operation in order to avoid backflows.
  • a preferred depth T of the heating channels 7a-c of a few millimeters, in particular 1 to 5 mm, and a preferred width B of a few centimeters, in particular 20 to 40 mm, and an average circumference of 1.6 m, for example, results in a speed of the air in the heating channels of 100 to 250 m / s and a volume throughput of 0.004 to 0.04 m3 / s at the selected pressures.
  • the heating power required for the heating 22 and supplied via a heating supply line 23 is of the order of 50 to 200 kW.
  • the pressure of the air at outlet 20 (FIG. 5) is approximately 0.1 MPa.
  • the invention results in a compressor which is suitable for a warm start without loss of efficiency.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
EP94111521A 1993-08-14 1994-07-23 Compresseur ainsi que sa méthode de fonctionnement Expired - Lifetime EP0638727B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4327376A DE4327376A1 (de) 1993-08-14 1993-08-14 Verdichter sowie Verfahren zu dessen Betrieb
DE4327376 1993-08-14

Publications (2)

Publication Number Publication Date
EP0638727A1 true EP0638727A1 (fr) 1995-02-15
EP0638727B1 EP0638727B1 (fr) 1998-05-13

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EP94111521A Expired - Lifetime EP0638727B1 (fr) 1993-08-14 1994-07-23 Compresseur ainsi que sa méthode de fonctionnement

Country Status (4)

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US (1) US5605437A (fr)
EP (1) EP0638727B1 (fr)
JP (1) JP2956023B2 (fr)
DE (2) DE4327376A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19643716A1 (de) * 1996-10-23 1998-04-30 Asea Brown Boveri Schaufelträger für einen Verdichter
US6978622B2 (en) 2001-10-30 2005-12-27 Alstom Technology Ltd Turbomachine
US7329084B2 (en) 2001-10-30 2008-02-12 Alstom Technology Ltd Turbomachine
FR2943093A1 (fr) * 2009-03-16 2010-09-17 Snecma Dispositif de reglage de la position radiale et/ou axiale d'une virole de stator de turbomachine
FR3096071A1 (fr) * 2019-05-16 2020-11-20 Safran Aircraft Engines Contrôle de jeu entre des aubes de rotor d’aéronef et un carter

Families Citing this family (22)

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Publication number Priority date Publication date Assignee Title
JPH1061457A (ja) * 1996-08-27 1998-03-03 Mitsubishi Heavy Ind Ltd 複合サイクル発電プラント用ガスタービン
US6626635B1 (en) * 1998-09-30 2003-09-30 General Electric Company System for controlling clearance between blade tips and a surrounding casing in rotating machinery
US6190127B1 (en) * 1998-12-22 2001-02-20 General Electric Co. Tuning thermal mismatch between turbine rotor parts with a thermal medium
EP1046787B1 (fr) * 1999-04-23 2006-06-07 General Electric Company Circuit de chauffage et de refroidissement d'un boîtier intérieur d'une turbine
US6379108B1 (en) 2000-08-08 2002-04-30 General Electric Company Controlling a rabbet load and air/oil seal temperatures in a turbine
US6401460B1 (en) * 2000-08-18 2002-06-11 Siemens Westinghouse Power Corporation Active control system for gas turbine blade tip clearance
US6435823B1 (en) 2000-12-08 2002-08-20 General Electric Company Bucket tip clearance control system
US7128522B2 (en) * 2003-10-28 2006-10-31 Pratt & Whitney Canada Corp. Leakage control in a gas turbine engine
EP1566531A1 (fr) * 2004-02-19 2005-08-24 Siemens Aktiengesellschaft Turbine à gas avec carter protégé contre le refroidessement et Méthode de fonctionnement d'une turbine à gas
US7434402B2 (en) * 2005-03-29 2008-10-14 Siemens Power Generation, Inc. System for actively controlling compressor clearances
US7708518B2 (en) * 2005-06-23 2010-05-04 Siemens Energy, Inc. Turbine blade tip clearance control
DE502005008377D1 (de) * 2005-07-01 2009-12-03 Siemens Ag Gekühlte Gasturbinenleitschaufel für eine Gasturbine, Verwendung einer Gasturbinenleitschaufel sowie Verfahren zum Betreiben einer Gasturbine
US8172521B2 (en) * 2009-01-15 2012-05-08 General Electric Company Compressor clearance control system using turbine exhaust
US8210801B2 (en) * 2009-01-29 2012-07-03 General Electric Company Systems and methods of reducing heat loss from a gas turbine during shutdown
WO2013141938A1 (fr) 2011-12-30 2013-09-26 Rolls-Royce North American Technologies, Inc. Commande de jeu d'extrémité de turbine à gaz
US9127558B2 (en) 2012-08-01 2015-09-08 General Electric Company Turbomachine including horizontal joint heating and method of controlling tip clearance in a gas turbomachine
US20140230400A1 (en) * 2013-02-15 2014-08-21 Kevin M. Light Heat retention and distribution system for gas turbine engines
EP2818646A1 (fr) * 2013-06-28 2014-12-31 Siemens Aktiengesellschaft Turbine à gaz comportant un carter de compresseur avec une ouverture d'entrée servant à tempérer le carter du compresseur et utilisation de la turbine à gaz
US10392950B2 (en) * 2015-05-07 2019-08-27 General Electric Company Turbine band anti-chording flanges
US10138752B2 (en) * 2016-02-25 2018-11-27 General Electric Company Active HPC clearance control
US10947993B2 (en) * 2017-11-27 2021-03-16 General Electric Company Thermal gradient attenuation structure to mitigate rotor bow in turbine engine
US11879411B2 (en) 2022-04-07 2024-01-23 General Electric Company System and method for mitigating bowed rotor in a gas turbine engine

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US1541834A (en) * 1924-04-21 1925-06-16 Losel Franz Axial turbine
BE649186A (fr) * 1963-06-12 1964-10-01
GB2103718A (en) * 1981-08-03 1983-02-23 Nuovo Pignone Spa Gas turbine plant
JPS5857100A (ja) * 1981-09-30 1983-04-05 Hitachi Ltd 翼端すきま調整式の軸流圧縮機
JPH02153232A (ja) * 1988-12-02 1990-06-12 Hitachi Ltd ガスタービンケーシングの加熱装置
EP0541325A1 (fr) * 1991-11-04 1993-05-12 General Electric Company Contrôle thermique du jeu d'extrémités d'aubes de turbines à gaz

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JPS60247001A (ja) * 1984-05-23 1985-12-06 Hitachi Ltd 蒸気タ−ビンケ−シングの熱応力制御装置
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FR2614073B1 (fr) * 1987-04-15 1992-02-14 Snecma Dispositif d'ajustement en temps reel du jeu radial entre un rotor et un stator de turbomachine
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US1541834A (en) * 1924-04-21 1925-06-16 Losel Franz Axial turbine
BE649186A (fr) * 1963-06-12 1964-10-01
GB2103718A (en) * 1981-08-03 1983-02-23 Nuovo Pignone Spa Gas turbine plant
JPS5857100A (ja) * 1981-09-30 1983-04-05 Hitachi Ltd 翼端すきま調整式の軸流圧縮機
JPH02153232A (ja) * 1988-12-02 1990-06-12 Hitachi Ltd ガスタービンケーシングの加熱装置
EP0541325A1 (fr) * 1991-11-04 1993-05-12 General Electric Company Contrôle thermique du jeu d'extrémités d'aubes de turbines à gaz

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PATENT ABSTRACTS OF JAPAN vol. 7, no. 145 (M - 224) 24 June 1983 (1983-06-24) *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19643716A1 (de) * 1996-10-23 1998-04-30 Asea Brown Boveri Schaufelträger für einen Verdichter
US5967743A (en) * 1996-10-23 1999-10-19 Asea Brown Boveri Ag Blade carrier for a compressor
US6978622B2 (en) 2001-10-30 2005-12-27 Alstom Technology Ltd Turbomachine
US7329084B2 (en) 2001-10-30 2008-02-12 Alstom Technology Ltd Turbomachine
FR2943093A1 (fr) * 2009-03-16 2010-09-17 Snecma Dispositif de reglage de la position radiale et/ou axiale d'une virole de stator de turbomachine
FR3096071A1 (fr) * 2019-05-16 2020-11-20 Safran Aircraft Engines Contrôle de jeu entre des aubes de rotor d’aéronef et un carter
US11319830B2 (en) 2019-05-16 2022-05-03 Safran Aircraft Engines Control of clearance between aircraft rotor blades and a casing

Also Published As

Publication number Publication date
EP0638727B1 (fr) 1998-05-13
JP2956023B2 (ja) 1999-10-04
DE4327376A1 (de) 1995-02-16
US5605437A (en) 1997-02-25
DE59405943D1 (de) 1998-06-18
JPH0763192A (ja) 1995-03-07

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