EP0838595B1 - Support pour aube pour un compresseur - Google Patents

Support pour aube pour un compresseur Download PDF

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Publication number
EP0838595B1
EP0838595B1 EP97810716A EP97810716A EP0838595B1 EP 0838595 B1 EP0838595 B1 EP 0838595B1 EP 97810716 A EP97810716 A EP 97810716A EP 97810716 A EP97810716 A EP 97810716A EP 0838595 B1 EP0838595 B1 EP 0838595B1
Authority
EP
European Patent Office
Prior art keywords
blade carrier
cooling
compressor
ring
carrier according
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
EP97810716A
Other languages
German (de)
English (en)
Other versions
EP0838595A3 (fr
EP0838595A2 (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
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
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 for a thermal highly loaded high pressure compressor, the blade carrier is provided with cooling channels, which are in a closed circuit are flowed through by 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 known from BE-A 549 186 between a system for the blade carrier and external insulation consisting of pipes, channels, lines and the like circular or to arrange spirally around the blade carrier, to this by supplying external heat at any time on a Maintain target temperature.
  • a temperature control of the compressor housing in which the temperature of the compressor housing is lowered in a controlled manner by a more or less strong flow of cooling air or cooling water.
  • the cooling air is removed 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 cooling water acts on an annular space between an inner housing enclosing the rotor and an outer housing.
  • a sensor for measuring the gap width is connected on the output side to the cooling water feed pump. Depending on the sensor signal, the cooling water is applied to the inner housing.
  • 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 is ensures that the rotor temperature remains lower than the temperature the combustion air in the respective section at the compressor outlet. In this case, the radial operating cycles bigger than the games when the system is cold, because the rotor temperature is lower than the blade carrier temperature.
  • the basis of the invention The idea is to raise the blade carrier to approx. 70 ° C To cool down to 120 ° C and thus during all operating conditions only a negligible thermal movement to subjugate. This would only make the mechanical and thermal movements of the rotor and take it into account minimal radial play can be achieved in all operating conditions. In particular, the warm start is not a criterion more for the right choice of radial play.
  • this is the beginning of a blade carrier mentioned type achieved in that the blade carrier is equipped with cooling channels, which in the circumferential direction ring-shaped or helical within the blade carrier run and with their inlets and outlets a coherent Form skeleton, which shed with the shovel carrier is.
  • Water is a suitable coolant; possibly could also use a cooling gas or high pressure steam as a coolant Be considered.
  • each cooling ring is provided with a feed line and a discharge line in the form of a ring, so that at least two separate cooling paths can be provided. It then makes sense that at least every second successive cooling ring or at least every second successive loop of the helical arrangement is connected to a separate cooling path in the longitudinal direction of the blade carrier.
  • a single-shaft gas turbine is shown schematically in FIG. which in the example with reheating is equipped.
  • the rotor 10 and the rotor are Blade carrier 11 with a single-stage high-pressure blading 12 or a multi-stage (not shown) Low pressure blading equipped. That of the primary combustion chamber 13 escaping flue gas relaxes under power in the high-pressure blading 12 and reaches a mixing section 25. There is the flue gas via a fuel supply additional fuel and possibly combustion air are added and the mixture is fed to a second combustion chamber.
  • 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 blades 18a, 19a, which are turned of the rotor 10 are shoveled. on the other hand are the associated guide vanes 18b, 19b in turns the two-part 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 is believed to result from the combustion air the compression in the low pressure blading at their Outlet already has a temperature of approx. 450 ° C. From Fig.
  • thermally highly loaded blade carrier 21 In order for the thermally highly loaded blade carrier 21 to be an inexpensive one To be able to use material is on the diffuser wall a heat shield 23 attached in a suitable manner.
  • the outside of the blade carrier is against the plenum 14 21 in their entire axial extent over a thermal insulation 24 delimited in the form of a cover plate.
  • the blade carrier is also over its entire length 21 is provided with cooling channels 26, which in closed Circulated by a coolant, here water are. These cooling channels 26 run inside in the circumferential direction of the blade carrier 21 and are in direct current to the compressor flow flows through.
  • FIG. 2 An example of a suitable cooling channel arrangement is shown Fig. 2.
  • the channels 26 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 from a pressure vessel 32, which in turn supplied with water by means of a pressure pump 33 becomes.
  • a gas atmosphere Located above the water level in the pressure vessel a gas atmosphere. From the last cooling rings the water is discharged via a water return line 34 and recooled in a heat exchanger 35 before it enters 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.
  • Orifices 36 are to be supplied evenly with water arranged upstream of the cooling rings 27 acted upon first.
  • the cooling paths are designed such that every second Cooling ring 27 from the arrangement lies in the same path. How out Fig. 2 recognizable, the first ring 27a draws water from the left supply line 28a. The water flows through the ring 27a in Counterclockwise and is derived from the lead 29a Ring 27a discharged. This derivative 29a communicates via a Connection line 37 with the supply of the next Cooling ring 27. Accordingly, 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 again via a connecting line 37 to the supply line of the cooling ring after next 27. In the longitudinal direction of the blade carrier 21 are adjacent cooling channels 26 in opposite directions flows through.
  • this solution offers the advantage that all cooling rings 27 with their supply and discharge lines 28 and 29 and the connecting lines 37 compiled into a skeleton construction can be, for example, by welding. This Skeleton construction can subsequently be carried out with the shovel carrier 21 are shed together.
  • material for the blade carrier 21 offers ductile iron, for example GGG40Mo or cast iron.
  • the cooling rings 27 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 during the Always an intimate contact and therefore a good heat exchange guaranteed between the blade carrier and cooling pipes.
  • 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. 6) just like pins 42 (Fig. 5).
  • 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 21 to be cooled, steel tubes with an outer diameter of 20 mm are selected.
  • the thermal insulation of the blade carrier 21 is dimensioned such that the temperature difference between the outside and the inside of the blade carrier 21 should not be greater than 30 K-70 K.
  • the heat transfer due to convection between the combustion air and the blade carrier 21 should be limited to 50-150 W / m 2 K.
  • cooling channel arrangement can be therein exist that the cooling channels 26 are arranged helically and that here too 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 its own closing and Derivatives connected to a separate cooling path his.
  • 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 21 are and closed with a welded cover band 38 become.
  • a circular or helical channel arrangement are used.
  • the Inlets and outlets of the individual channels 26a and the connecting lines would in this case be outside of the actual Blade carrier 21 are located.
  • As material for the Blade carrier 21 then offers a low-alloy steel on. At 39, they are on the inner wall of the blade carrier 21 provided rotations for the compressor guide vanes 18b designated.
  • the cooling channels could also flow through in counterflow to the compressor flow. Likewise, flowing through all cooling channels in the same direction either clockwise or counterclockwise does not leave the scope of the invention.
  • 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)

Claims (7)

  1. Support d'aube pour un compresseur axial (17), de préférence pour un compresseur à haute pression à forte charge thermique, dans lequel le support d'aube (21) est pourvu de canaux de refroidissement (26) qui sont parcourus en un circuit fermé par un agent de refroidissement, caractérisé en ce que les canaux de refroidissement (26, 26a) sont disposés sous forme annulaire ou hélicoïdale dans le sens périphérique à l'intérieur du support d'aube (21) et forment avec leurs conduites d'arrivée et de retour (28, 29) une structure continue, qui est moulée dans le support d'aube (21).
  2. Support d'aube selon la revendication 1, caractérisé en ce qu'avec une disposition annulaire des canaux de refroidissement (26, 26a), chaque anneau de refroidissement (27) est pourvu d'une conduite d'arrivée (28) et d'une conduite de retour (29).
  3. Support d'aube selon la revendication 1, caractérisé en ce qu'avec une disposition hélicoïdale, il est prévu au moins deux chemins de refroidissement séparés.
  4. Support d'aube selon la revendication 1, caractérisé en ce que des canaux de refroidissement (26, 26a) voisins dans le sens longitudinal du support d'aube (21) sont parcourus en sens contraire.
  5. Support d'aube selon la revendication 1, caractérisé en ce qu'au moins un anneau de refroidissement (27) sur deux anneaux successifs dans le sens longitudinal du support d'aube (21) ou au moins une boucle sur deux boucles successives dans le sens longitudinal est raccordé(e) à un chemin de refroidissement séparé.
  6. Support d'aube selon la revendication 5, caractérisé en ce qu'avec plusieurs chemins de refroidissement, un diaphragme (36) est disposé dans la conduite d'arrivée de l'eau (30).
  7. Support d'aube selon la revendication 1, caractérisé en ce que les canaux de refroidissement (26, 26a) sont parcourus dans le même sens que l'écoulement dans le compresseur.
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 EP0838595A2 (fr) 1998-04-29
EP0838595A3 EP0838595A3 (fr) 1998-11-25
EP0838595B1 true 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)

Families Citing this family (14)

* 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
EP1446556B1 (fr) * 2001-10-30 2006-03-29 Alstom Technology Ltd Turbomachine
DE10233113A1 (de) * 2001-10-30 2003-05-15 Alstom Switzerland Ltd Turbomaschine
DE102004041271A1 (de) * 2004-08-23 2006-03-02 Alstom Technology Ltd Einrichtung und Verfahren zum Kühlen eines Gehäuses einer Gasturbine bzw. einer Brennkammer
EP2148045A1 (fr) * 2008-07-25 2010-01-27 Siemens Aktiengesellschaft Section de boîtier pour une turbine à gaz
EP2159384A1 (fr) * 2008-08-27 2010-03-03 Siemens Aktiengesellschaft Support statorique d'aubes directrices pour une turbine à gaz
EP2513431A1 (fr) * 2009-12-17 2012-10-24 Volvo Aero Corporation Agencement et procédé pour le refroidissement à circuit fermé d'un composant de moteur de turbine à gaz
FR3101915B1 (fr) * 2019-10-11 2022-10-28 Safran Helicoptere Engines Anneau de turbine de turbomachine comprenant des conduites internes de refroidissement
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
US20240309779A1 (en) * 2023-03-14 2024-09-19 Raytheon Technologies Corporation Compressor case with a cooling cavity

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Also Published As

Publication number Publication date
JPH10131896A (ja) 1998-05-19
US5967743A (en) 1999-10-19
CN1091849C (zh) 2002-10-02
DE19643716A1 (de) 1998-04-30
EP0838595A3 (fr) 1998-11-25
CN1186181A (zh) 1998-07-01
DE59710300D1 (de) 2003-07-24
EP0838595A2 (fr) 1998-04-29

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