EP2310748A2 - Dispositif de bouclier thermique - Google Patents

Dispositif de bouclier thermique

Info

Publication number
EP2310748A2
EP2310748A2 EP09761668A EP09761668A EP2310748A2 EP 2310748 A2 EP2310748 A2 EP 2310748A2 EP 09761668 A EP09761668 A EP 09761668A EP 09761668 A EP09761668 A EP 09761668A EP 2310748 A2 EP2310748 A2 EP 2310748A2
Authority
EP
European Patent Office
Prior art keywords
heat shield
seal
groove
support structure
shield assembly
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
EP09761668A
Other languages
German (de)
English (en)
Other versions
EP2310748B1 (fr
Inventor
Marcus ZURHORST
Jens Kleinfeld
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Publication of EP2310748A2 publication Critical patent/EP2310748A2/fr
Application granted granted Critical
Publication of EP2310748B1 publication Critical patent/EP2310748B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the invention relates to a heat shield assembly consisting of a support structure and a heat shield attached thereto with a voltage applied to the support structure, circumferential side wall wherein the side wall at least partially has a groove and an inner space facing the support structure and defined by groove and sidewall groove edges.
  • the invention further relates to a combustion chamber having a heat shield assembly, and a gas turbine having such a combustion chamber.
  • US Pat. No. 6,470,685 B2 discloses a heat shield arrangement having a first heat shield and a second heat shield adjacent thereto, leaving a gap.
  • the individual heat shields are attached to a support structure, so that in each case an interior space is limited.
  • On the hot wall side of a heat shield a plurality of projecting into the interior of the rods are mounted, which allow better cooling of the heat shield from the interior.
  • the side walls of the heat shields are extended with an additional element, ie the side walls are located directly on the support structure on. In order to allow air to escape from the interior, cooling holes are introduced in the side walls.
  • GB 2 298 266 A discloses a heat shield assembly with heat shields overlapping in the end regions. This thus forms a complete coverage of the wall to be protected from hot gas. At least one side wall of each heat shield lies with at least one contact point directly on the support structure. In order to allow air to escape, cooling holes are introduced both in the hot side of the heat shields and in the side walls.
  • EP 1 507 116 A1 has a heat shield arrangement which comprises a plurality of heat shields arranged next to one another on a support structure while leaving a gap, wherein one or each heat shield is mounted on a support structure, so that an interior space is formed. Through an inlet channel coolant flows into the interior.
  • the side walls are not directly on the support structure, but are connected via a respective seal with the support structure.
  • the sealing element connects directly to the side wall, i. It represents a direct extension of this side wall dar. The thus extended side wall is located on the
  • the sealing element thereby fulfill both a sealing function for the coolant and a mechanical damping function for the heat shield assembly.
  • a sealing function for the coolant for the exit of the coolant from the interior of adeffenauslass- channel is provided, which opens into the gap.
  • the known heat shields are based on the principle that the heat shield walls rest directly on the support structure during the assembly of the heat shields.
  • For the cooling of the heat shields there are cooling openings which lead from the heat shield interior into the combustion chamber.
  • the coolant is completely or partially passed through the cooling holes in this gap.
  • the object of the invention is to provide an improved in terms of cooling efficiency heat shield assembly, which is characterized by an increase in efficiency.
  • the heat shield assembly should be usable in a combustion chamber for gas turbines.
  • a heat shield assembly consisting of a support structure and an attached heat shield with a voltage applied to the support structure, circumferential side wall wherein the side wall at least partially has a groove and an inner space facing the support structure and defined by groove and sidewall groove edges wherein the groove comprises a seal having at least two opposite edges, wherein the seal is clamped in the groove such that the at least two opposite edges are bent into the groove edges upon mounting of the heat shield on the support structure, such that rolling of the seal on the support structure is ensured, whereby a sealing function is ensured even during operation.
  • the invention is based on the observation that at the high temperatures required for the combustion in the heat shields discussed above, thermally-induced occur so that the corners of the heat shields are pressed against the support structure.
  • the hot-side center of the heat shields arches up.
  • the individual sides of the heat shields resting on the support structure, which form the side wall, likewise bulge away from the support structure in such a way that the side center of the support structure is now spaced apart by a thermally-induced gap.
  • a seal is mounted in the groove.
  • the seal is strained so that the two edges point away from the support side.
  • these edges are pressed into the Nutkanten, that is bent to the side wall of the heat shield.
  • the sealing function is guaranteed, so to speak, by the clamping of the seal in the groove edges, since the groove edges hold the seal in its desired position. Due to the shape of the gasket clamped in this way, it is unrolled on the entire support structure.
  • the thermally induced gap is optimally closed.
  • the bias counteracts a thermal warping, as would be effected at a temperature gradient occurring with a non-preloaded seal.
  • the heat shield bulges in the operating state. In this condition, essentially only the four heat shield ceilings remain in contact with the supporting structure. This has the effect that, in the critical operating state, the seal is, so to speak, held down in the groove edges, that is, remains in its previously desired position. This ensures the correct seat of the seal in all operating conditions, the function of the seal thus always ensured.
  • the seal can fulfill its function optimally, as it always remains in the desired position.
  • the coolant is essentially usually give as cooling air, which is wholly or partially removed from the compressor, which is arranged downstream of the combustion chamber.
  • the seal is completely embedded in the groove.
  • the seal is tightened particularly sure-fire-proof.
  • the seal is an elastic bending strip. This one can be particularly well stretched and in the Groove be introduced and is easy to manufacture.
  • the strip may also be tubular.
  • the seal is made of metal or metal alloy. This is particularly heat and temperature resistant.
  • the groove is arranged circumferentially over the entire side wall.
  • the groove is arranged in regions over the entire side wall. This can be decided depending on the type of heat shield and production factors.
  • the seal has a bending radius by the bracing.
  • FIG 3 top view of a cut-open heat shield with groove
  • FIG. 3 a schematic side view of a cut-open heat shield arrangement with a seal (planar)
  • 3b shows a schematic side view of a cut-open heat shield arrangement with a seal (concave)
  • 3c schematic side view of a cut-open heat shield arrangement with seal (convex) 4 shows a schematic drawing of the forces acting on the heat shield and the seal during operation
  • a gas turbine has an upstream compressor for combustion air, an intermediate combustion chamber and a turbine for driving the compressor and a generator or a work machine, not shown.
  • the combustion chamber comprises a support structure on which heat shield assemblies are attached.
  • the heat shield assembly 1 shows an example of a heat shield arrangement 1 in the case of thermal deformation according to the prior art.
  • the heat shield assembly 1 has a support structure 2 and a heat shield 3 with a hot side 5.
  • a side wall 4 is inclined relative to the hot side 5.
  • the heat shield arrangement 1 forms an interior 10, which is supplied with cooling medium 14, preferably cooling air, which is taken from a compressor, from the side of the support structure 2 through the supply channels 15.
  • cooling medium 14 preferably cooling air, which is taken from a compressor, from the side of the support structure 2 through the supply channels 15.
  • cooling medium 14 preferably cooling air, which is taken from a compressor
  • a thermally induced curvature 12 occurs between the support structure 2 and the side wall 4 in the heat shield 3.
  • a heat-induced gap 13 occurs between the support structure 2 and the side wall 4 in the heat shield 3.
  • Through this coolant 14 escapes unhindered into the combustion chamber.
  • 2 shows a heat shield assembly 1 on a support structure 2 with groove 7 and groove edges.
  • FIG 3 shows a plan view of a cut-open heat shield with a groove 7.
  • the groove 7 is arranged in regions.
  • the groove edges 16 are defined by the groove 7 and the side wall 4.
  • the heat-shielded ceilings 22 remain on the support structure 2, while the centers of the side walls 4 bulge so that they can release a gap 13 through the coolant 14.
  • FIG. 3a shows a schematic side view of a cutaway heat shield arrangement with a seal 6 (planar support structure).
  • a groove 7 with the groove edges 16 is present.
  • the seal has edges 8 (ends).
  • the seal 6 with the edges 8 is introduced into the groove 16.
  • the seal 6 is shaped such that the edges 8 of the seal 6 in the groove edges 16 is up. If now the heat shield 3 is mounted over the seal 6, the edges 8 are pressed into the groove edges 16, that is, bent to the side wall 4. Thus, the seal 6 is clamped in the groove 7. Due to the distortion, the seal 6 has a bending radius 20.
  • the bending radius 20 of the seal 6 is smaller than the radius of the sealing surface in planar (FIG 3a) or convex (FIG 3b) to be sealed surfaces.
  • the bending radius 20 of the seal 6 is greater than the radius of the sealing surface. Therefore, it is unrolled by the shape of the seal 6 on the support structure 2.
  • the heat shield 3 bulges. In this state, essentially only at the heat ceiling 22, it has contact with the support structure 2.
  • the thermally induced gap 14 is optimally closed.
  • the bias causes the seal 6 to become in use, i. Do not warp when exposed to temperature, as would happen, for example, with a non-strained component. Since the heat shield 3 has contact with the support structure 2 on the heat cable covers 22 in every operating state, this ensures a correct seat in each of the operating states. Thus, the seal 6 thus always remains in its predetermined, desired position and can therefore optimally fulfill its sealing function.
  • a seal 6 may for example consist of a thin bent metal strip or a thin bent metal tube.
  • FIG 4 shows a schematic drawing of the forces acting on the heat shield 1 and the seal 6 in operation.
  • the force F acts on the heat shield ceilings 22 and presses them onto the support structure 2.
  • the seal 6 is unrolled on the support structure 2.
  • the bias causes a fixed, desired position of the seal 6 under all operating conditions.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Abstract

La présente invention concerne un dispositif de bouclier thermique (1) composé d'une structure de support (2) et d'un bouclier thermique (3) fixé à ladite structure et comprenant une paroi latérale continue (4) qui repose sur la structure de support (2). La paroi latérale (4) présente au moins par endroits une rainure (7), ainsi qu'un espace intérieur (10) qui fait face à la structure de support (2) et des bords de rainure (16) qui sont définis par la rainure (7) et la paroi latérale (4). La rainure (7) comprend un joint (6) qui présente au moins deux bords opposés (8). Le joint (6) est contraint dans la rainure (7) de telle façon que les deux bords opposés (8) sont courbés dans les bords de rainure (16) lorsque le bouclier thermique (3) est monté sur la structure de support (2), ce qui permet de dérouler le joint (6) sur la structure de support (2) et d'assurer ainsi une fonction d'étanchéité également pendant le fonctionnement. L'invention concerne aussi une chambre de combustion comprenant ledit dispositif de bouclier thermique, ainsi qu'une turbine à gaz.
EP09761668.4A 2008-06-12 2009-06-05 Dispositif de bouclier thermique Active EP2310748B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200810028025 DE102008028025B4 (de) 2008-06-12 2008-06-12 Hitzeschildanordnung
PCT/EP2009/056943 WO2009150105A2 (fr) 2008-06-12 2009-06-05 Dispositif de bouclier thermique

Publications (2)

Publication Number Publication Date
EP2310748A2 true EP2310748A2 (fr) 2011-04-20
EP2310748B1 EP2310748B1 (fr) 2017-02-01

Family

ID=41066167

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09761668.4A Active EP2310748B1 (fr) 2008-06-12 2009-06-05 Dispositif de bouclier thermique

Country Status (5)

Country Link
EP (1) EP2310748B1 (fr)
CN (1) CN102066840A (fr)
DE (1) DE102008028025B4 (fr)
RU (1) RU2508507C2 (fr)
WO (1) WO2009150105A2 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102400721B (zh) * 2011-11-01 2014-04-02 沈阳黎明航空发动机(集团)有限责任公司 一种涡轮支承支点隔热屏的更换方法

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE831620C (de) * 1949-04-25 1952-02-14 Roland Laraque Verbesserung an Brennkraftmaschinen mit einander gegenueberliegenden Zylindern
GB2166120A (en) * 1984-09-15 1986-04-30 Yeate And Hanson Ind Ltd Linings
EP0550126A1 (fr) * 1992-01-02 1993-07-07 General Electric Company Bouclier thermique pour post-combusteur
GB2298266A (en) 1995-02-23 1996-08-28 Rolls Royce Plc A cooling arrangement for heat resistant tiles in a gas turbine engine combustor
GB2300909B (en) * 1995-05-18 1998-09-30 Europ Gas Turbines Ltd A gas turbine gas duct arrangement
WO1998013645A1 (fr) * 1996-09-26 1998-04-02 Siemens Aktiengesellschaft Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds
EP1022437A1 (fr) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Elément de construction à l'usage d'une machine thermique
US6302402B1 (en) * 1999-07-07 2001-10-16 Air Products And Chemicals, Inc. Compliant high temperature seals for dissimilar materials
GB2361303B (en) 2000-04-14 2004-10-20 Rolls Royce Plc Wall structure for a gas turbine engine combustor
DE10205180B4 (de) * 2002-02-08 2005-04-28 Elringklinger Ag Kühlwasserabdichtung zwischen einem Motorblock und einer Zylinderlaufbuchse
EP1507116A1 (fr) 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
DE102005046731A1 (de) * 2005-04-19 2006-11-02 Siemens Ag Hitzeschildanordnung
GB2434199B (en) * 2006-01-14 2011-01-05 Alstom Technology Ltd Combustor liner with heat shield

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009150105A2 *

Also Published As

Publication number Publication date
DE102008028025A1 (de) 2009-12-24
EP2310748B1 (fr) 2017-02-01
WO2009150105A2 (fr) 2009-12-17
WO2009150105A3 (fr) 2011-01-06
RU2508507C2 (ru) 2014-02-27
RU2011100155A (ru) 2012-07-20
CN102066840A (zh) 2011-05-18
DE102008028025B4 (de) 2011-05-05

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