EP3587743B1 - Dispositif de refroidissement d'un carter de turbomachine - Google Patents

Dispositif de refroidissement d'un carter de turbomachine Download PDF

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Publication number
EP3587743B1
EP3587743B1 EP19182042.2A EP19182042A EP3587743B1 EP 3587743 B1 EP3587743 B1 EP 3587743B1 EP 19182042 A EP19182042 A EP 19182042A EP 3587743 B1 EP3587743 B1 EP 3587743B1
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EP
European Patent Office
Prior art keywords
casing
plate
edges
collection box
turbomachine
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.)
Active
Application number
EP19182042.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3587743A1 (fr
Inventor
Jacques Marcel Arthur Bunel
Etienne Gérard Joseph CANELLE
Emeric Christian Amaury D'herbigny
Pierrick Bernard Jean
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.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP3587743A1 publication Critical patent/EP3587743A1/fr
Application granted granted Critical
Publication of EP3587743B1 publication Critical patent/EP3587743B1/fr
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Classifications

    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium

Definitions

  • the subject of the invention is a device for cooling a turbomachine casing by a flow of gas.
  • a method widely used for adjusting the clearances in turbomachines, between the fixed and mobile blades on the one hand, the rotor and the stator to which they are attached on the other hand, consists in blowing a flow of fresh gas on the stator housing. to produce thermal shrinkage of its diameter.
  • the flow is generally a small part of the flow of gases from the vein of the turbomachine, which is withdrawn from compressors where the gas is at high pressure and still fresh, which is allowed to circulate in conduits along the vein and that we blow on the much hotter turbines of the machine.
  • the device traditionally comprises annular ramps surrounding the stator casing at a distance from it and provided with blowing orifices directed towards the casing.
  • the document US 6,149,074 A describes such a cooling device.
  • a disadvantage of this device is a lack of precision.
  • the position of the ramp cannot always be kept optimal because of the deformations, in particular the differential thermal expansions due to different heating, undergone by the machine during operation and the manufacturing tolerances of the blowing device comprising the ramps.
  • These differential deformations and expansions may amount to moving the ramps both in the axial direction and in the radial direction of the casing, especially since the latter is generally conical.
  • the ramps can thus be located next to the places of the casing which were supposed to undergo the blowing (normally the most rigid parts, around the circular ribs which stiffen it, and which determines these dimensions well), and their distance from the casing can also be out of order, and even disappear in certain situations.
  • a device in which the ramps are assembled to the housing is the subject of the document EP 2236772 A2 .
  • the ramps are made up of an interior sheet provided with the blowing openings, an exterior sheet delimiting a blowing chamber with the interior sheet, and an intermediate sheet allowing equalization of the air flows towards the blowing openings. These sheets are provided with superimposed edges and screwed to retaining lugs on the casing.
  • the structure is relatively complex, and positional errors, sufficiently large in this field where very high precision is desired, risk appearing in the absence of special precautions during assembly.
  • the invention is therefore based mainly on the connection to the casing of the end of the blowing device, that is to say the sheet through which the gas is blown, which is parallel to the casing and maintained at a constant distance and well. determined by the casing, thanks to the two stop supports obtained in perpendicular directions.
  • the geometric blowing conditions thus remain uniform regardless of the changes in the operation of the machine and the deformations undergone by the various parts, which do not affect this almost indeformable junction of the casing and the end of the blowing device.
  • the protruding reliefs on the casing may be provided with discharge openings.
  • the collector box comprises edges respectively parallel to the edges of the sheet and placed on them; this arrangement, especially if the sheet comprises a first essentially plane edge and a second edge essentially perpendicular to the first edge, makes it possible to easily assemble the collector box to the sheet.
  • the connector is elbow and sliding through a wall of the housing, a wall of the capacity or both, which makes it possible to compensate for differential expansions in the directions of the sliding movement, or possibly any direction.
  • Another aspect of the invention is a turbomachine comprising such a cooling device, the sheet then being able to advantageously be situated around a portion of the casing which is provided with a circular rib.
  • the cooling device may also comprise a plurality of sheets and manifold boxes respectively associated with the sheets, the sheets and boxes form successive rings around the casing in the axial direction of the casing.
  • a turbomachine turbine comprises a casing 1 around an axial direction X.
  • the casing 1 comprises a skin 2 of conical shape regularly reinforced by circular ribs 3 and which therefore define more rigid annular portions of the casing 1.
  • a cooling device comprises rings 4 surrounding the casing 1, resting on circular bands of the skin 2 and preferably mounted in front of the ribs 3.
  • the rings 4 are connected to a fresh gas tank, here an air supply box 5, which extends at some distance from them, by fittings 6 having an elbow shape.
  • the figure 2 shows in detail one of the rings 4 of the device. It comprises a sheet 7 of annular and conical shape, unitary in the axial direction X (possibly composed of angular sectors assembled together) placed on the skin 2 while being mounted around it and a collector box 8 covering the sheet 7.
  • the figure 3 shows that the sheet 7 comprises a main part 9, foraminous (crossing multiple holes) and two side edges 10 and 11.
  • the sheet 7 has the same taper as the portion of the skin 2 on which it extends, so that the main part 9 is parallel to the skin 2 and separated from it by a blowing chamber 12 of a constant depth of a few millimeters (for example 2 millimeters).
  • a first side edge 10 is essentially plane and extends perpendicular to the axial direction X , while the second side edge 11 (at a larger diameter of the sheet 7) is essentially cylindrical.
  • Skin 2 ( figure 4 ) is provided with two reliefs 13 and 14 rigid, annular and protrusions in the form of ribs, intended to receive the lateral edges 10 and 11 respectively in order to establish support or stop states.
  • the first lateral edge 10 abuts against a lateral face of the relief 13 which is flat and oriented in the axial direction X, while the second lateral edge 11 rests on an outer face, cylindrical and of the same diameter as it and oriented in the direction radial R, of the other relief 14.
  • the latter is provided with evacuation slots 15 regularly distributed over its circumference to allow the evacuation of the blowing chamber 12.
  • the collector housing 8 is also of annular shape and comprises ( figure 5 ) a first lateral edge 16 plane perpendicular to the axial direction X and a second lateral edge 17, opposite, directed in this axial direction X and cylindrical or slightly conical.
  • the side edges 16 and 17 respectively have the same directions as the side edges 10 and 11 of the sheet 7, and they can be laid on them and fixed to them by brazing, welding or otherwise.
  • the side edges 10 and 11 of the sheet 7 are likewise fixed to the reliefs 13 and 14 by brazing, welding or otherwise.
  • the collector housing 8 is furthermore formed of a continuous sheet between the side edges 16 and 17, which is bulging outward in the radial direction R and opens only on the inner radial side, where the collector housing 8 covers the main part 9 of the sheet 7. The latter therefore separates the blowing chamber 12 from a distribution chamber 18 located outside radially to it and delimited by the manifold housing 8.
  • the wall of the collector box 8 is however pierced at the location of the connector 6.
  • the latter passes through it by an axial branch 19 and is connected to the supply box 5 by passing through its wall by another branch 20 oblique and separated from the previous by an elbow 21.
  • the ends of the branches 19 and 20 penetrate into the collector housing 8 and the supply housing 5 by junctions which allow to slide through their walls, in order to accommodate the device to variations in positions, due for example to thermal expansions in the machine, in particular between the housing 1 and the power supply unit 5.
  • a single connector 6 has been shown between the supply unit 5 and each of the rings 4.
  • Several connectors 6 could be provided for each of the rings 4, distributed around their circumference. It would then be advisable to compartmentalize the inside of the manifold boxes 8 by partitions, in order to ensure equal flow therein.
  • the supply unit 5, common to all the connections 6, is connected to the compressor of the machine, or possibly to another source of compressed air, by a pipe 22 which has only been sketched out here.
  • the compressed air withdrawn from the compressors arrives in the supply box 5 through the pipe 22, then is distributed by the fittings 6 in the manifold boxes 8 and is distributed in angular direction in their distribution chambers 18, then passes through the sheets 7 by their holes to enter the blowing chambers and lick the skin 2 at the location of the stiffeners 3, before being discharged to the outside through the slots 15.
  • the uniform depth of the blowing chambers 12 guarantees that the air flows lick each portion of the skin 2 invariably, which makes it possible to predict the thermal shrinkages that are imposed with good precision.
  • the value of the flow rate can conventionally be regulated by a valve placed for example on the pipe 22.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19182042.2A 2018-06-25 2019-06-24 Dispositif de refroidissement d'un carter de turbomachine Active EP3587743B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1855680A FR3082872B1 (fr) 2018-06-25 2018-06-25 Dispositif de refroidissement d'un carter de turbomachine

Publications (2)

Publication Number Publication Date
EP3587743A1 EP3587743A1 (fr) 2020-01-01
EP3587743B1 true EP3587743B1 (fr) 2021-06-16

Family

ID=63145095

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19182042.2A Active EP3587743B1 (fr) 2018-06-25 2019-06-24 Dispositif de refroidissement d'un carter de turbomachine

Country Status (4)

Country Link
US (1) US11047259B2 (zh)
EP (1) EP3587743B1 (zh)
CN (1) CN110630343B (zh)
FR (1) FR3082872B1 (zh)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6563312B2 (ja) * 2015-11-05 2019-08-21 川崎重工業株式会社 ガスタービンエンジンの抽気構造
FR3085719B1 (fr) * 2018-09-06 2021-04-16 Safran Aircraft Engines Boitier d'alimentation en air sous pression d'un dispositif de refroidissement par jets d'air
FR3112811B1 (fr) * 2020-07-23 2022-07-22 Safran Aircraft Engines Turbine à cavités pressurisées
CN111927579B (zh) * 2020-07-31 2022-09-06 中国航发贵阳发动机设计研究所 一种涡轮机匣热变形调节结构及调节方法

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US4019320A (en) * 1975-12-05 1977-04-26 United Technologies Corporation External gas turbine engine cooling for clearance control
US4513567A (en) * 1981-11-02 1985-04-30 United Technologies Corporation Gas turbine engine active clearance control
FR2540939A1 (fr) * 1983-02-10 1984-08-17 Snecma Anneau d'etancheite pour un rotor de turbine d'une turbomachine et installation de turbomachine munie de tels anneaux
US5273396A (en) * 1992-06-22 1993-12-28 General Electric Company Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud
FR2766232B1 (fr) 1997-07-18 1999-08-20 Snecma Dispositif de refroidissement ou d'echauffement d'un carter circulaire
FR2766517B1 (fr) * 1997-07-24 1999-09-03 Snecma Dispositif de ventilation d'un anneau de turbomachine
DE19855130A1 (de) * 1998-11-30 2000-05-31 Abb Alstom Power Ch Ag Kühlbarer Mantel einer Gasturbine oder dergleichen
FR2803871B1 (fr) * 2000-01-13 2002-06-07 Snecma Moteurs Agencement de reglage de diametre d'un stator de turbine a gaz
FR2816352B1 (fr) * 2000-11-09 2003-01-31 Snecma Moteurs Ensemble de ventilation d'un anneau de stator
FR2819010B1 (fr) * 2001-01-04 2004-05-28 Snecma Moteurs Secteur d'entretoise de support d'anneau de stator de la turbine haute pression d'une turbomachine avec rattrapage de jeux
JP2005513330A (ja) * 2001-12-13 2005-05-12 アルストム テクノロジー リミテッド ガスタービンの高温ガス流路構造体
US6899518B2 (en) * 2002-12-23 2005-05-31 Pratt & Whitney Canada Corp. Turbine shroud segment apparatus for reusing cooling air
US8801370B2 (en) * 2006-10-12 2014-08-12 General Electric Company Turbine case impingement cooling for heavy duty gas turbines
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FR3040429B1 (fr) * 2015-08-27 2019-06-07 Safran Aircraft Engines Dispositif de fixation des rampes de refroidissement par jets d'air du carter d'une turbine de turbomachine
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Also Published As

Publication number Publication date
CN110630343B (zh) 2023-03-28
FR3082872B1 (fr) 2021-06-04
US20190390569A1 (en) 2019-12-26
CN110630343A (zh) 2019-12-31
US11047259B2 (en) 2021-06-29
EP3587743A1 (fr) 2020-01-01
FR3082872A1 (fr) 2019-12-27

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