EP1205637A1 - Kühlungsvorrichtung für einen Statorring - Google Patents

Kühlungsvorrichtung für einen Statorring Download PDF

Info

Publication number: EP1205637A1
Authority: EP; European Patent Office
Prior art keywords: stator ring; ramps; ring; ventilation assembly; shells
Prior art date: 2000-11-09
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

EP01402865A

Other languages

English (en)

French (fr)

Other versions

EP1205637B1 (de

Inventor

Jean-Baptiste Arilla

Thierry Fachat

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

SNECMA Moteurs SA

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.)

2000-11-09

Filing date

2001-11-08

Publication date

2002-05-15

2001-11-08 Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA

2002-05-15 Publication of EP1205637A1 publication Critical patent/EP1205637A1/de

2003-07-09 Application granted granted Critical

2003-07-09 Publication of EP1205637B1 publication Critical patent/EP1205637B1/de

2021-11-08 Anticipated expiration legal-status Critical

Status Expired - Lifetime legal-status Critical Current

Links

238000001816 cooling Methods 0.000 title 1
238000009423 ventilation Methods 0.000 claims description 18
239000007789 gas Substances 0.000 claims description 5
238000007664 blowing Methods 0.000 claims description 2
125000006850 spacer group Chemical group 0.000 claims description 2
230000000712 assembly Effects 0.000 description 2
238000000429 assembly Methods 0.000 description 2
230000010339 dilation Effects 0.000 description 2
238000004519 manufacturing process Methods 0.000 description 2
238000000034 method Methods 0.000 description 2
240000000966 Allium tricoccum Species 0.000 description 1
230000009286 beneficial effect Effects 0.000 description 1
230000006835 compression Effects 0.000 description 1
238000007906 compression Methods 0.000 description 1
238000006073 displacement reaction Methods 0.000 description 1
238000009826 distribution Methods 0.000 description 1
230000000694 effects Effects 0.000 description 1
238000012423 maintenance Methods 0.000 description 1
238000003825 pressing Methods 0.000 description 1
230000029058 respiratory gaseous exchange Effects 0.000 description 1
238000007789 sealing Methods 0.000 description 1
238000003466 welding Methods 0.000 description 1

Images

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
- 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
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/60—Assembly methods
- F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
- F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

This talk deals with a set of ventilation of a stator ring, intended to convey a gas at a determined temperature up to a ring turbomachine stator to adjust its diameter and the game he will do with blade tips of rotor rotating in it.
Such ventilation assemblies are commonly used in turbojets and consist of multi-branched conduits taken up and the ends of which are provided with holes to blow gas and especially air to a large number of points, judiciously distributed, of the ring.
Terminal conduits are very often ramps running around the rings, in the shape of an arc of a circle and embracing part of their perimeter. Often too, the gas is blown in the axial direction, on outer ribs of the ring rather than on the ring itself, so that the diameter is controlled by these ribs which are more rigid and govern therefore the deformations of the ring proper.
the assembly which will be described here is characterized in that it is easy to manufacture, despite the large number of conduits that are generally required use, and assemble to the ring despite the complications which can arise from dilations differential thermal at different times of machine operation.
the invention thus relates to a ventilation assembly of a ring stator composed of branched conduits comprising supply lines, distributors and ramps adjacent to the ring and provided with holes blowing of gases directed towards the ring, characterized in what the ramps are made up of pairs of half shells including a flange and a border surrounding the flange, the pairs of half-shells being joined by the edges, the distributors include spool coils between the ramps and fitted with end edges shaped to fit on side cheek openings of the flanges.
a stator ring 1 is associated with a group of ventilation units 2 conforming to the invention, each of which occupies a portion of the circumference of ring 1 and includes a group of ramps 3 parallel and in an arc, distributor 4 for distributing air from ventilation between all ramps 3 and a duct supply 5 (visible in Figure 2) connected to the distributor 4.
supply lines 5 join after one or more others distributors, which are not shown because they are not the subject of this invention; this one relates more specifically to the end of the assemblies ventilation 2, i.e. their parts which are close to ring 1 to be ventilated.
each of the ramps 3 is composed of a half-shell left 7 and a right half shell 8 of which each of these is assembled to one of these. More precisely, the half-shells 7 and 8 of the two genera each include a flange 9 substantially flat and a border 10 established around the flange 9, the borders 10 of pairs of half-shells 7 and 8 additional being extended and joined to form a single ramp.
Half-shells 7 and 8 can be made by simple operation stamping and the connections between the borders 10 can be performed by welding. This mode of manufacturing is extremely simple and avoids having to machine tubes to bring them to shapes and desired dimensions, which would probably be a lot more tedious.
half-shells of left 7 can generally be built at from the same tool as the right half-shells 8 which are symmetrical to the previous ones by the plane of seal.
This overall similarity does not exclude some dissimilarities of details.
half-shells 7 and 8 could be constructed with borders 10 of different widths, so for example favor ventilation by the 3 most wide.
An example of application of this process appears in Figure 2, where three ramps 3 ventilate two ribs 11, the central ramp being placed between the two ribs 11 and ventilating them both, which justifies that its width is double.
the distributor 4 also includes coils 15 in the form of a short cylinder serving spacers between the ramps 3 and with the conduit 5. It is often beneficial that they are similar, but they can also be different in particular in length. They understand generally edges 16 to be engaged in the openings 13 ramps 3 to hold them in place, and flanges 17 pressing on the ramps 3 to define the spacing of these. Distributor 4 is formed when the coils 15 have been soldered to ramps 3. However, the distribution duct 5 remains generally separate from dispenser 4 and can slide in the input coil 15, a seal sealing 18 being added between them, however.
one of the coils 15 comprises planar faces and opposite 19 enclosing the end 20 (here enlarged) of the rib 11 which the corresponding coil 15 overcomes.
the reduction in the axial clearance between the coil 15 and the enlarged portion of the rib 11 contributes to ensuring the axial positioning of the distributors 4 on the ring 1.
the second coil overlaps its ring with axial play, this to allow the relative dilations between the housings 4 and casing 1 without generating a connection hyperstatic and unwanted constraints.
FIG. 3 shows that the end 20 of this rib 11 has a v-notch 21 in which the central, cylindrical portion of the coil 15 rests in self-centering, which guarantees the distributor 4 against radial movements and tangents to ring 1: perfect positioning radial, tangential and in orientation along the axis of the engine is performed.
Brackets 22 are linked to one end of the stator ring 1 by fixing bolts 23 and include a wing 24 under one end of the ruler 6; the other end of it is placed on a boss 25 of the stator ring 1.
Bolts 26 and 27 are screwed to wing 24 and boss 25. They maintain the ends of rule 6 on them by compressing springs 28 based on rule 6 by washers 29.
Such an assembly has the property of allow better control of the support effort of rules 6 on equettes 24 and 25. If this effect is excessive, the assembly is rigid and does not allow thermal respiration.
rule 6 to which ramps 3 are welded, is provided with 30 wide openings around bolts 26 and 27, so that it can be move by sliding axially and tangentially by compared to the stator ring. This flexible mounting avoids therefore to produce excessive internal stresses in ventilation assembly 2, since the ramps 3 have the ability to move above the ring 1 without exerting too much effort. These relative displacements are generally due to thermal expansions differential.
the support of one of the coils 15 against the end 20 of the corresponding rib 11 offers also some flexibility by allowing all of ventilation 2 to move to the ends, while being recalled towards the stator ring 1 and the bottom of the vé 21 by springs 28. This flexibility is valuable by absorbing expansions inevitable differential thermal with such equipment.

Landscapes

Engineering & Computer Science (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Motor Or Generator Cooling System (AREA)
Motor Or Generator Frames (AREA)
Structures Of Non-Positive Displacement Pumps (AREA)
Turbine Rotor Nozzle Sealing (AREA)
Iron Core Of Rotating Electric Machines (AREA)

EP01402865A 2000-11-09 2001-11-08 Belüftungsvorrichtung für einen Statorring Expired - Lifetime EP1205637B1 (de)

Applications Claiming Priority (2)

Application Number	Priority Date	Filing Date	Title
FR0014373A FR2816352B1 (fr)	2000-11-09	2000-11-09	Ensemble de ventilation d'un anneau de stator
FR0014373		2000-11-09

Publications (2)

Publication Number	Publication Date
EP1205637A1 true EP1205637A1 (de)	2002-05-15
EP1205637B1 EP1205637B1 (de)	2003-07-09

Family

ID=8856230

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP01402865A Expired - Lifetime EP1205637B1 (de)	2000-11-09	2001-11-08	Belüftungsvorrichtung für einen Statorring

Country Status (9)

Country	Link
US (1)	US6896038B2 (de)
EP (1)	EP1205637B1 (de)
JP (1)	JP3913032B2 (de)
CA (1)	CA2361103C (de)
DE (1)	DE60100448T2 (de)
ES (1)	ES2199921T3 (de)
FR (1)	FR2816352B1 (de)
RU (1)	RU2276733C2 (de)
UA (1)	UA73938C2 (de)

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EP1577502A1 (de) *	2004-03-18	2005-09-21	Snecma	Einrichtung um die Spaltweite zwischen den Schaufelspitzen und dem Gehäuse einer Gasturbine zu Steuern
EP1577501A1 (de) *	2004-03-18	2005-09-21	Snecma	Hochdruckturbinenstator einer Strömungsmaschine und deren Zusammenbauverfahren
EP2243931A3 (de) *	2009-04-16	2013-09-18	Rolls-Royce plc	Turbinengehäusekühlung
ITTO20120519A1 (it) *	2012-06-14	2013-12-15	Avio Spa	Turbina a gas per motori aeronautici
FR2999642A1 (fr) *	2012-12-17	2014-06-20	Snecma	Ensemble statorique dont les bosses comportent des portions en creux ou en saillie
CN106382136A (zh) *	2016-11-18	2017-02-08	中国科学院工程热物理研究所	一种跨音速动叶叶顶间隙主动控制装置
FR3040428A1 (fr) *	2015-08-27	2017-03-03	Snecma	Dispositif de refroidissement par jets d'air du carter d'une turbine d'une turbomachine
CN107923259A (zh) *	2015-08-27	2018-04-17	赛峰飞机发动机公司	用于附接通过空气射流冷却涡轮发动机的涡轮机的外壳的歧管的装置
EP3318725A1 (de) *	2016-11-08	2018-05-09	Safran Aircraft Engines	Anschlussanordnung für die kühlung einer turbine einer strömungsmaschine
EP3415724A1 (de) *	2017-06-12	2018-12-19	United Technologies Corporation	Elastische montageanordnung für einen turbinenmotor
FR3089544A1 (fr) *	2018-12-10	2020-06-12	Safran Aircraft Engines	Dispositif de refroidissement d’un carter de turbomachine
FR3099798A1 (fr) *	2019-08-09	2021-02-12	Safran Aircraft Engines	Ensemble pour une turbine de turbomachine
FR3099801A1 (fr) *	2019-08-09	2021-02-12	Safran Aircraft Engines	Ensemble pour une turbine de turbomachine
WO2021209713A1 (fr)	2020-04-17	2021-10-21	Safran Aircraft Engines	Dispositif de refroidissement d'un carter de turbine

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FR2829525B1 (fr) *	2001-09-13	2004-03-12	Snecma Moteurs	Assemblage de secteurs d'un distributeur de turbine a un carter
FR2865237B1 (fr) *	2004-01-16	2006-03-10	Snecma Moteurs	Perfectionnements apportes aux dispositifs de controle de jeu dans une turbine a gaz
US7597537B2 (en) *	2005-12-16	2009-10-06	General Electric Company	Thermal control of gas turbine engine rings for active clearance control
US7503179B2 (en) *	2005-12-16	2009-03-17	General Electric Company	System and method to exhaust spent cooling air of gas turbine engine active clearance control
US7785063B2 (en) *	2006-12-15	2010-08-31	Siemens Energy, Inc.	Tip clearance control
US7914254B2 (en) *	2007-02-13	2011-03-29	General Electric Company	Integrated support/thermocouple housing for impingement cooling manifolds and cooling method
FR2931872B1 (fr) *	2008-05-28	2010-08-20	Snecma	Turbine haute pression d'une turbomachine avec montage ameliore du boitier de pilotage des jeux radiaux d'aubes mobiles.
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FR2977276B1 (fr) *	2011-06-30	2016-12-09	Snecma	Agencement pour le raccordement d'un conduit a un boitier de distribution d'air
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US10330012B2 (en) *	2014-02-04	2019-06-25	United Technologies Corporation	Brackets for gas turbine engine components
RU2567892C1 (ru) *	2014-06-02	2015-11-10	Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России)	Статор компрессора высокого давления
US9869196B2 (en) *	2014-06-24	2018-01-16	General Electric Company	Gas turbine engine spring mounted manifold
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US10513944B2 (en) *	2015-12-21	2019-12-24	General Electric Company	Manifold for use in a clearance control system and method of manufacturing
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FR3058459B1 (fr)	2016-11-04	2018-11-09	Safran Aircraft Engines	Dispositif de refroidissement pour une turbine d'une turbomachine
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FR3079874B1 (fr) *	2018-04-09	2020-03-13	Safran Aircraft Engines	Dispositif de refroidissement pour une turbine d'une turbomachine
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FR3082872B1 (fr) *	2018-06-25	2021-06-04	Safran Aircraft Engines	Dispositif de refroidissement d'un carter de turbomachine
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FR3089545B1 (fr) *	2018-12-07	2021-01-29	Safran Aircraft Engines	Dispositif de refroidissement d’un carter de turbine pour une turbomachine
FR3122694B1 (fr) *	2021-05-07	2024-03-29	Safran Aircraft Engines	Turboréacteur muni d’un ensemble de fixation disposé sur un carter de soufflante
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US12416243B2 (en)	2023-03-24	2025-09-16	General Electric Company	Seal support assembly for a turbine engine
US12372002B2 (en)	2023-03-24	2025-07-29	General Electric Company	Seal support assembly for a turbine engine
US12215588B2 (en)	2023-03-27	2025-02-04	General Electric Company	Seal assembly for a gas turbine engine
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US5399066A (en) *	1993-09-30	1995-03-21	General Electric Company	Integral clearance control impingement manifold and environmental shield

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2000
- 2000-11-09 FR FR0014373A patent/FR2816352B1/fr not_active Expired - Fee Related
2001
- 2001-10-26 JP JP2001328678A patent/JP3913032B2/ja not_active Expired - Fee Related
- 2001-11-06 CA CA002361103A patent/CA2361103C/en not_active Expired - Fee Related
- 2001-11-08 US US09/986,280 patent/US6896038B2/en not_active Expired - Lifetime
- 2001-11-08 EP EP01402865A patent/EP1205637B1/de not_active Expired - Lifetime
- 2001-11-08 UA UA2001117658A patent/UA73938C2/uk unknown
- 2001-11-08 RU RU2001130175/06A patent/RU2276733C2/ru not_active IP Right Cessation
- 2001-11-08 DE DE60100448T patent/DE60100448T2/de not_active Expired - Lifetime
- 2001-11-08 ES ES01402865T patent/ES2199921T3/es not_active Expired - Lifetime

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US4279123A (en) *	1978-12-20	1981-07-21	United Technologies Corporation	External gas turbine engine cooling for clearance control
US5100291A (en) *	1990-03-28	1992-03-31	General Electric Company	Impingement manifold
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
US5399066A (en) *	1993-09-30	1995-03-21	General Electric Company	Integral clearance control impingement manifold and environmental shield

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
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EP1577502A1 (de) *	2004-03-18	2005-09-21	Snecma	Einrichtung um die Spaltweite zwischen den Schaufelspitzen und dem Gehäuse einer Gasturbine zu Steuern
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EP1205637B1 (de)	2003-07-09
JP3913032B2 (ja)	2007-05-09
DE60100448T2 (de)	2004-04-15
FR2816352B1 (fr)	2003-01-31
US6896038B2 (en)	2005-05-24
FR2816352A1 (fr)	2002-05-10
CA2361103A1 (en)	2002-05-09
ES2199921T3 (es)	2004-03-01
RU2276733C2 (ru)	2006-05-20
UA73938C2 (uk)	2005-10-17
JP2002195007A (ja)	2002-07-10
CA2361103C (en)	2009-12-29
US20020053837A1 (en)	2002-05-09
DE60100448D1 (de)	2003-08-14

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