EP3587743A1 - Vorrichtung zum kühlen eines turbotriebwerkgehäuses - Google Patents

Vorrichtung zum kühlen eines turbotriebwerkgehäuses Download PDF

Info

Publication number: EP3587743A1
Authority: EP; European Patent Office
Prior art keywords: casing; sheet; edges; turbomachine; reliefs
Prior art date: 2018-06-25
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

EP19182042.2A

Other languages

English (en)

French (fr)

Other versions

EP3587743B1 (de

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

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.)

2018-06-25

Filing date

2019-06-24

Publication date

2020-01-01

2019-06-24 Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS

2020-01-01 Publication of EP3587743A1 publication Critical patent/EP3587743A1/de

2021-06-16 Application granted granted Critical

2021-06-16 Publication of EP3587743B1 publication Critical patent/EP3587743B1/de

Status Active legal-status Critical Current

2039-06-24 Anticipated expiration legal-status Critical

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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
- F01D25/14—Casings modified therefor
- 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
- 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 widely used method for adjusting the clearances in turbomachines, between the fixed and movable vanes on the one hand, the rotor and the stator to which they are fixed on the other hand, consists in blowing a flow of fresh gas on the stator casing to produce a 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 drawn off in 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 device in which the ramps are assembled to the housing is the subject of the document EP 2236772 A2 .
the ramps are composed of an inner sheet provided with the blowing orifices, an outer sheet delimiting a blowing chamber with the inner sheet, and an intermediate sheet allowing an equalization of the air flows towards the blowing orifices. These sheets are provided with overlapping flanges and screwed to retaining tabs on the housing.
the structure is relatively complex, and positional faults, sufficiently large in this area where very high precision is desired, risk appearing in the absence of special precautions during assembly.
a device for cooling a turbomachine revolution casing by a gas flow comprising: a sheet metal surrounding a circular band of the casing, having edges fixed to the casing and a foraminated main part parallel to the casing , the sheet and the casing defining a gas blowing chamber provided with discharge openings; a collecting box surrounding the sheet, and delimiting with the sheet a gas distribution chamber by covering the main part of the sheet; a gas supply capacity remote from the housing; and at least one connection conduit connecting the capacitor to the housing; and the device is characterized in that the position of the sheet on the casing is ensured by protruding reliefs from the latter, to serve as supports or stops at the edges of the sheet; and that the reliefs provide a stop in axial direction of the casing at a first of the edges of the sheet and a support in radial direction of the casing at a second of the edges of the sheet.
the invention is therefore mainly based on the connection to the housing of the end of the blowing device, that is to say the sheet through which the gas is blown, which is parallel to the housing and kept at a constant distance and well determined from the housing, thanks to the two abutment supports obtained in perpendicular directions.
the geometrical blowing conditions thus remain uniform whatever the operating evolutions of the machine and the deformations undergone by the various parts, which do not affect this roughly non-deformable junction of the casing and of the end of the blowing device.
the protruding reliefs on the casing can be provided with discharge openings.
the manifold housing includes edges respectively parallel to the edges of the sheet and placed on them; this arrangement, especially if the sheet includes a first essentially planar edge and a second edge essentially perpendicular to the first edge, makes it easy to assemble the manifold housing to the sheet.
the connector is bent 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 advantageously being able to be located around a portion of the casing which is provided with a circular rib.
the cooling device can 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 strips of the skin 2 and preferably mounted in front of the ribs 3.
the rings 4 are connected to a fresh gas capacity, here an air supply box 5, which extends some distance from them, by fittings 6 having a bent shape.
the figure 2 represents 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 collecting box 8 covering the sheet 7.
the figure 3 shows that the sheet 7 comprises a main part 9, foraminated (crossed by multiple bores) and two lateral edges 10 and 11.
the sheet 7 has the same conicity 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 with a constant depth of a few millimeters (for example 2 millimeters).
a first lateral edge 10 is essentially plane and extends perpendicular to the axial direction X , while the second lateral edge 11 (at a larger diameter of the sheet 7) is essentially cylindrical.
Skin 2 ( figure 4 ) is provided with two rigid reliefs 13 and 14, annular and protrusions in the form of ribs, intended to receive the lateral edges 10 and 11 respectively to establish support or stop states.
the first lateral edge 10 abuts against a lateral face of the relief 13 which is plane and oriented in the axial direction X, while the second lateral edge 11 is supported 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 collecting box 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 placed on them and fixed to them by soldering, welding or otherwise.
the lateral edges 10 and 11 of the sheet 7 are likewise fixed to the reliefs 13 and 14 by brazing, welding or otherwise.
the manifold housing 8 is also formed of a continuous sheet between the lateral edges 16 and 17, which is curved outward in the radial direction R and opens only on the inner radial side, at the place where the manifold 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 radially to it externally and delimited by the manifold housing 8.
the wall of the manifold housing 8 is however pierced at the location of the connector 6.
the latter passes through it through an axial branch 19 and is connected to the supply housing 5 by crossing its wall by another oblique branch 20 separated from the previous by a bend 21.
the ends of the branches 19 and 20 penetrate into the collecting box 8 and the supply box 5 by junctions which allow them to slide through their walls, in order to accommodate the device at variations in positions, due for example to thermal expansion in the machine, in particular between the casing 1 and the power supply unit 5.
connection 6 has been shown between the power supply unit 5 and each of the rings 4.
connections 6 could be provided for each of the rings 4, distributed around their circumference. It would then be advisable to compartmentalize the interior of the manifold boxes 8 by partitions, in order to ensure equal flows 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 outlined here.
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 through their holes to enter the blowing chambers and lick the skin 2 at the location of the stiffeners 3, before being discharged 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 retractions that are imposed with good precision.
the value of the flow rate can conventionally be adjusted by a valve placed for example on the pipe 22.

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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 Vorrichtung zum kühlen eines turbotriebwerkgehäuses Active EP3587743B1 (de)

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 true EP3587743A1 (de)	2020-01-01
EP3587743B1 EP3587743B1 (de)	2021-06-16

Family

ID=63145095

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP19182042.2A Active EP3587743B1 (de)	2018-06-25	2019-06-24	Vorrichtung zum kühlen eines turbotriebwerkgehäuses

Country Status (4)

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

Families Citing this family (7)

* 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
DE102023121051A1 (de) *	2023-08-08	2025-02-13	MTU Aero Engines AG	Kühlbares Turbinenmodul und erwärmbares Verdichtermodul für eine Strömungsmaschine, sowie Strömungsmaschine
CN116927899A (zh) *	2023-08-24	2023-10-24	南京航空航天大学	一种高压涡轮机匣结构
FR3153847A1 (fr) *	2023-10-04	2025-04-11	Safran Aircraft Engines	Dispositif de refroidissement d’un carter de turbomachine

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US6149074A (en)	1997-07-18	2000-11-21	Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"	Device for cooling or heating a circular housing
EP1914392A2 (de) *	2006-10-12	2008-04-23	General Electric Company	Turbinengehäuse-Prallkühlung für Hochleistungsgasturbinen
US20080206042A1 (en) *	2006-11-30	2008-08-28	Ching-Pang Lee	Methods and system for recuperated circumferential cooling of integral turbine nozzle and shroud assemblies
EP2236772A2 (de)	2009-03-26	2010-10-06	Pratt & Whitney Canada Corp.	Gasturbinentriebwerk mit Vorrichtung zur aktiven Steuerung des Schaufelspitzenspiels und zugehöriges Betriebsverfahren
FR2972760A1 (fr) *	2011-03-16	2012-09-21	Snecma	Anneau de carter de turbomachine

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2018
- 2018-06-25 FR FR1855680A patent/FR3082872B1/fr active Active
2019
- 2019-06-24 US US16/449,573 patent/US11047259B2/en active Active
- 2019-06-24 EP EP19182042.2A patent/EP3587743B1/de active Active
- 2019-06-25 CN CN201910554329.5A patent/CN110630343B/zh active Active

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US6149074A (en)	1997-07-18	2000-11-21	Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"	Device for cooling or heating a circular housing
EP1914392A2 (de) *	2006-10-12	2008-04-23	General Electric Company	Turbinengehäuse-Prallkühlung für Hochleistungsgasturbinen
US20080206042A1 (en) *	2006-11-30	2008-08-28	Ching-Pang Lee	Methods and system for recuperated circumferential cooling of integral turbine nozzle and shroud assemblies
EP2236772A2 (de)	2009-03-26	2010-10-06	Pratt & Whitney Canada Corp.	Gasturbinentriebwerk mit Vorrichtung zur aktiven Steuerung des Schaufelspitzenspiels und zugehöriges Betriebsverfahren
FR2972760A1 (fr) *	2011-03-16	2012-09-21	Snecma	Anneau de carter de turbomachine

Also Published As

Publication number	Publication date
FR3082872B1 (fr)	2021-06-04
US20190390569A1 (en)	2019-12-26
US11047259B2 (en)	2021-06-29
CN110630343B (zh)	2023-03-28
FR3082872A1 (fr)	2019-12-27
EP3587743B1 (de)	2021-06-16
CN110630343A (zh)	2019-12-31

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