EP0838595A2 - Support pour aube pour un compresseur - Google Patents

Support pour aube pour un compresseur Download PDF

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Publication number
EP0838595A2
EP0838595A2 EP97810716A EP97810716A EP0838595A2 EP 0838595 A2 EP0838595 A2 EP 0838595A2 EP 97810716 A EP97810716 A EP 97810716A EP 97810716 A EP97810716 A EP 97810716A EP 0838595 A2 EP0838595 A2 EP 0838595A2
Authority
EP
European Patent Office
Prior art keywords
blade carrier
cooling
cooling channels
carrier according
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
EP97810716A
Other languages
German (de)
English (en)
Other versions
EP0838595B1 (fr
EP0838595A3 (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.)
General Electric Switzerland GmbH
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0838595A2 publication Critical patent/EP0838595A2/fr
Publication of EP0838595A3 publication Critical patent/EP0838595A3/fr
Application granted granted Critical
Publication of EP0838595B1 publication Critical patent/EP0838595B1/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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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

Definitions

  • the invention relates to a blade carrier for an axially flowed through compressor, preferably a thermally highly stressed High pressure compressor, the blade carrier with Cooling channels is provided, which in a closed circuit of are flowed through a coolant.
  • Cooled or heated blade carriers for turbomachinery are well known.
  • the start-up problems of a steam turbine to solve it is already from BE-A 649 186 known, between the blade carrier and an outer insulation a system consisting of pipes, channels, lines and the like circular or spiral around the blade carrier to arrange around this by supplying external heat to keep at a set temperature at all times.
  • the reduction in radial play is made more difficult that are in different operating states of the compressor Rotor blades and compressor housing in different Expand or contract mass.
  • the radial play must therefore be chosen so that it is under the most unfavorable operating conditions, i.e. with extensive Rotor and blades and compressed compressor housing, is still sufficient. It must be taken into account that the change in radial play is both mechanical can also have thermal causes.
  • As a mechanical The main cause is the radial deflection of the Rotors and the blades through the at fast rotation attacking centrifugal forces in question.
  • thermal causes are different thermal expansions in the rotor and stator due to temperature differences or different Expansion coefficient of the materials used view as well as the ovalization of the housing parts through the parting line in the parting line.
  • the rotor can also be cooled in modern gas turbines be and are made of ferritic material. Then he is in usually provided with thermal insulation that ensures that the rotor temperature remains lower than the temperature of the combustion air in the respective section at the compressor outlet. In this case, the radial ones Operating games larger than the games when cold System because the rotor temperature is lower than the blade carrier temperature.
  • this is the case of a blade carrier achieved at the outset in that the cooling channels at least approximately in the circumferential direction within the blade carrier get lost, and yourself in a closed Water cycle are located, which essentially consists of a Circulation pump, a pressure vessel and a heat exchanger consists.
  • Water is a suitable coolant; Possibly could also be considered a cooling gas or high pressure steam Coolants should be considered.
  • cooling channels are annular or are arranged helically and if each cooling ring with a supply line and a discharge line is provided, so that at least two separate cooling paths can be provided. It then lends itself to that in the longitudinal direction of the blade carrier at least every second successive cooling ring or at least every second consecutive loop of the helical arrangement on a separate cooling path connected.
  • cooling ducts with their supply and discharge lines are connected Form skeleton, so this can be in the mold of the blade carrier and introduced together with the blade carrier be shed.
  • cooling channels in a blade carrier pour in.
  • this is cooling of gas turbine blades, for which purpose in the axial direction of the machine running and communicating with the guide vane feet Tubes are arranged in the blade carrier.
  • a single-shaft gas turbine is shown schematically in FIG. which in the example with reheating is equipped.
  • the rotor 10 is the rotor 10 and Blade carrier 11 with a single-stage high-pressure blading 12 or one (not shown) multi-stage Low pressure blading equipped. That of the primary combustion chamber 13 escaping flue gas relaxes under power in the high-pressure blading and gets into one Mixing section 25. There is the flue gas via a fuel supply additional fuel and possibly combustion air admixed and the mixture of a second combustion chamber fed.
  • the primary combustion chamber 13 draws the combustion air from the Plenum 14 and is via the fuel line 15 with liquid and / or gaseous fuel.
  • the combustion air enters the plenum 14 from the diffuser 16 of the compressor 17. Its multi-stage high-pressure blading 18 or low-pressure blading 19 becomes on the one hand formed by moving blades, which in turns of the rotor 10 are shoveled. On the other hand, they are associated guide vanes in twists of two parts trained low pressure blade carrier 20 and high pressure blade carrier 21 attached. Between high-pressure blading 18 and low pressure blading 19 is a cooling air extraction 22 arranged. To represent the prevailing problem it is believed that the combustion air due to compression in the low-pressure blading at their outlet already has a temperature of approx. 450 ° C. From Fig.
  • a heat shield 23 in a suitable manner appropriate.
  • a thermal insulation 24 in the form of a cover plate delimited.
  • the blade carrier is also over its entire length is provided with cooling channels 26 which in closed loop of a coolant, here water, are flowed through. These cooling channels run in the circumferential direction inside the blade carrier and are in direct current flows through to the compressor flow.
  • FIG. 2 An example of a suitable cooling channel arrangement shows Fig. 2.
  • the channels are annular and exist from a plurality of side by side at a suitable distance, arranged cooling rings 27, each with a feed line 28 and a derivative 29.
  • the cooling rings 27 are fed via a water supply line 30 by means of a circulation pump 31.
  • the cooling water is drawn from a pressure holding vessel 32, which in turn by means of a pressure pump 33 with water is supplied. Above the water level in the pressure vessel there is a gas atmosphere. From the last The water is cooled by a water return line 34 removed and recooled in a heat exchanger 35, before it gets into the pressure vessel 32.
  • two separate cooling paths are provided, which is fed from the common water supply line 30 and when leaving the cooling channels in the common Water return line 34 open.
  • panels are to be supplied with water evenly 36 upstream of the cooling rings 27 applied first arranged.
  • the cooling paths are designed such that every second Cooling ring from the arrangement lies in the same path.
  • the first ring 27a draws water from the left supply line 28a.
  • the water flows through the ring in the Counterclockwise and is derived from the lead 29a Ring removed.
  • This derivative 29a communicates via a Connection line 37 with the supply line of the next Cooling ring.
  • the second ring 27b Water from the right supply line 28b.
  • the water flows through the ring here clockwise and is about the derivative 29b removed from the ring.
  • This derivative 29b communicates why about a connecting line 37 with the supply line of the cooling ring after next. In the longitudinal direction of the blade carrier neighboring cooling ducts become in opposite directions flows through.
  • this solution has the advantage that all cooling rings 27 with their inlets and outlets 28 resp. 29 and the connecting lines 37 compiled into a skeleton construction can be, for example, by welding. This Skeleton construction can subsequently be made using the shovel carrier be shed together.
  • Ductile iron is ideal, for example GGG40Mo or Cast iron.
  • the cooling rings are preferably made of steel pipes with a higher melting point than that of the blade carrier material. Due to the higher coefficient of thermal expansion of stainless steel is in operation Always an intimate contact and therefore a good heat exchange guaranteed between the blade carrier and cooling tubes.
  • the cooling pipes according to the figures 3 to 6 with their Aussenumfamg welded-on ribs 40, webs 41 or pins 42 be.
  • the ribs can be circular (Fig. 3) or be arranged helically (Fig. 4).
  • Longitudinal Crosspieces 41 can be attached to the pipe circumference in several places be (Fig. 5), just like pins 42 (Fig. 6).
  • a numerical example illustrates the mode of operation of the invention: with a wall thickness of approximately 50 to 70 mm of the blade carrier to be cooled, steel tubes with an outer diameter of 20 mm are selected.
  • the thermal insulation of the blade carrier is dimensioned such that the temperature difference between the outside and the inside of the blade carrier should not be greater than 30-70 ° C.
  • the heat transfer due to convection between the combustion air and the blade carrier should be limited to 50-150 W / m 2 K. In the case of a shovel carrier of a modern system, this means that a heat quantity of approx. 500 kW has to be dissipated via the closed water cooling circuit. If a temperature difference of 20 ° C between water inlet and water outlet is permitted, this requires a water volume of 6 kg / sec. It is advisable to work with a water pressure of 40 to 80 bar and a water temperature of maximum 120 ° C.
  • Another cooling channel arrangement can consist in that the cooling channels are arranged helically and that there are at least two separate cooling paths are provided. This solution corresponds to a two-course one Thread. Even then, every second would be consecutive Loop of the helical arrangement by means of own supply and discharge lines to a separate cooling path be connected.
  • FIG. 7 Another cooling channel arrangement shown in FIG. 7 can consist in that the cooling channels 26a by milling or Turning incorporated into the outer wall of the blade carrier are and closed with a welded cover band 38 will.
  • a circular or helical channel arrangement are used.
  • the Inlets and outlets of the individual channels and the connecting lines would in this case be outside the actual blade carrier are located.
  • As material for the The blade carrier then offers a low-alloy steel on. At 39, they are on the inner wall of the blade carrier attached screw holes for the compressor guide vanes designated.
  • the invention is of course not limited to the embodiment shown and described.
  • the cooling channels could also flow through in counterflow to the compressor flow.
  • flowing through all cooling channels in the same direction either clockwise or counterclockwise does not go outside the scope of the invention.
  • several cooling paths can of course also be provided instead of the two paths described. The right choice will be, among other things, a question of the permissible pressure loss within the cooling system.
  • the new cooling method is not only applicable to stationary gas turbines, but also, for example, to lightweight aircraft turbines. In this case, an aluminum or magnesium alloy is used as the material for the blade carrier to be cooled.

Landscapes

  • 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)
  • Turbine Rotor Nozzle Sealing (AREA)
EP97810716A 1996-10-23 1997-09-30 Support pour aube pour un compresseur Expired - Lifetime EP0838595B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19643716 1996-10-23
DE19643716A DE19643716A1 (de) 1996-10-23 1996-10-23 Schaufelträger für einen Verdichter

Publications (3)

Publication Number Publication Date
EP0838595A2 true EP0838595A2 (fr) 1998-04-29
EP0838595A3 EP0838595A3 (fr) 1998-11-25
EP0838595B1 EP0838595B1 (fr) 2003-06-18

Family

ID=7809543

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97810716A Expired - Lifetime EP0838595B1 (fr) 1996-10-23 1997-09-30 Support pour aube pour un compresseur

Country Status (5)

Country Link
US (1) US5967743A (fr)
EP (1) EP0838595B1 (fr)
JP (1) JPH10131896A (fr)
CN (1) CN1091849C (fr)
DE (2) DE19643716A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6978622B2 (en) 2001-10-30 2005-12-27 Alstom Technology Ltd Turbomachine
US7329084B2 (en) 2001-10-30 2008-02-12 Alstom Technology Ltd Turbomachine
EP2148045A1 (fr) * 2008-07-25 2010-01-27 Siemens Aktiengesellschaft Section de boîtier pour une turbine à gaz
WO2010023036A1 (fr) * 2008-08-27 2010-03-04 Siemens Aktiengesellschaft Support d'aubes directrices pour une turbine à gaz
FR3101915A1 (fr) * 2019-10-11 2021-04-16 Safran Helicoptere Engines Anneau de turbine de turbomachine comprenant des conduites internes de refroidissement

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
EP1046787B1 (fr) 1999-04-23 2006-06-07 General Electric Company Circuit de chauffage et de refroidissement d'un boîtier intérieur d'une turbine
US6398518B1 (en) * 2000-03-29 2002-06-04 Watson Cogeneration Company Method and apparatus for increasing the efficiency of a multi-stage compressor
US6435823B1 (en) 2000-12-08 2002-08-20 General Electric Company Bucket tip clearance control system
DE10131073A1 (de) * 2000-12-16 2002-06-20 Alstom Switzerland Ltd Vorrichtung zur Kühlung eines Deckbandes einer Gasturbinenschaufel
DE102004041271A1 (de) * 2004-08-23 2006-03-02 Alstom Technology Ltd Einrichtung und Verfahren zum Kühlen eines Gehäuses einer Gasturbine bzw. einer Brennkammer
WO2011075013A1 (fr) * 2009-12-17 2011-06-23 Volvo Aero Corporation Agencement et procédé pour le refroidissement à circuit fermé d'un composant de moteur de turbine à gaz
JP7271408B2 (ja) * 2019-12-10 2023-05-11 東芝エネルギーシステムズ株式会社 タービンロータ
US12158078B2 (en) 2023-03-14 2024-12-03 Rtx Corporation Compressor case with a cooling cavity

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE649186A (fr) 1963-06-12 1964-10-01
US4230436A (en) 1978-07-17 1980-10-28 General Electric Company Rotor/shroud clearance control system
US4386885A (en) 1980-05-19 1983-06-07 Bbc Brown Boveri & Company Limited Cooled guide support vane

Family Cites Families (21)

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DE451857C (de) * 1925-01-06 1927-11-02 Bernhard Moll Dipl Ing Dampfkraftanlage, insbesondere Dampfturbine, mit Vorwaermung des Kesselspeisewassers
DE1034193B (de) * 1957-10-26 1958-07-17 Escher Wyss Gmbh Verfahren zum Kuehlhalten hochbeanspruchter Teile von Dampf- oder Gasturbinen
CH425341A (de) * 1965-07-23 1966-11-30 Bbc Brown Boveri & Cie Gasturbine mit Kühlung der Schaufelträger
US3478689A (en) * 1967-08-02 1969-11-18 Borg Warner Circulating pump
US4069662A (en) * 1975-12-05 1978-01-24 United Technologies Corporation Clearance control for gas turbine engine
US4195474A (en) * 1977-10-17 1980-04-01 General Electric Company Liquid-cooled transition member to turbine inlet
CH636674A5 (de) * 1978-07-28 1983-06-15 Bbc Brown Boveri & Cie Geschlossener heizwasserkreislauf, insbesondere zur nutzung der abwaerme eines abhitzekessels, mit einer druckregeleinrichtung.
US4268221A (en) * 1979-03-28 1981-05-19 United Technologies Corporation Compressor structure adapted for active clearance control
JPS5857100A (ja) * 1981-09-30 1983-04-05 Hitachi Ltd 翼端すきま調整式の軸流圧縮機
US4431371A (en) * 1982-06-14 1984-02-14 Rockwell International Corporation Gas turbine with blade temperature control
US4632635A (en) * 1984-12-24 1986-12-30 Allied Corporation Turbine blade clearance controller
CN1003385B (zh) * 1985-04-15 1989-02-22 曼内斯曼股份公司 用于多级压缩机的冷却装置
JPH01315698A (ja) * 1988-06-15 1989-12-20 Toshiba Corp 軸流圧縮機
DE3943113A1 (de) * 1989-12-27 1991-07-04 Leybold Ag Geblaese oder pumpe mit vertikal angeordneter welle
US5167488A (en) * 1991-07-03 1992-12-01 General Electric Company Clearance control assembly having a thermally-controlled one-piece cylindrical housing for radially positioning shroud segments
US5167123A (en) * 1992-01-13 1992-12-01 Brandon Ronald E Flow condensing diffusers for saturated vapor applications
US5219268A (en) * 1992-03-06 1993-06-15 General Electric Company Gas turbine engine case thermal control flange
US5375973A (en) * 1992-12-23 1994-12-27 United Technologies Corporation Turbine blade outer air seal with optimized cooling
DE4327376A1 (de) * 1993-08-14 1995-02-16 Abb Management Ag Verdichter sowie Verfahren zu dessen Betrieb
JPH07317562A (ja) * 1994-05-25 1995-12-05 Mitsubishi Heavy Ind Ltd ガスタービン
DE4436731A1 (de) * 1994-10-14 1996-04-18 Abb Management Ag Verdichter

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE649186A (fr) 1963-06-12 1964-10-01
US4230436A (en) 1978-07-17 1980-10-28 General Electric Company Rotor/shroud clearance control system
US4386885A (en) 1980-05-19 1983-06-07 Bbc Brown Boveri & Company Limited Cooled guide support vane

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6978622B2 (en) 2001-10-30 2005-12-27 Alstom Technology Ltd Turbomachine
US7329084B2 (en) 2001-10-30 2008-02-12 Alstom Technology Ltd Turbomachine
EP2148045A1 (fr) * 2008-07-25 2010-01-27 Siemens Aktiengesellschaft Section de boîtier pour une turbine à gaz
WO2010023036A1 (fr) * 2008-08-27 2010-03-04 Siemens Aktiengesellschaft Support d'aubes directrices pour une turbine à gaz
FR3101915A1 (fr) * 2019-10-11 2021-04-16 Safran Helicoptere Engines Anneau de turbine de turbomachine comprenant des conduites internes de refroidissement

Also Published As

Publication number Publication date
JPH10131896A (ja) 1998-05-19
CN1091849C (zh) 2002-10-02
DE19643716A1 (de) 1998-04-30
EP0838595B1 (fr) 2003-06-18
EP0838595A3 (fr) 1998-11-25
US5967743A (en) 1999-10-19
DE59710300D1 (de) 2003-07-24
CN1186181A (zh) 1998-07-01

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