EP4058728A1 - Brennkammer mit keramischem hitzeschild und dichtung - Google Patents
Brennkammer mit keramischem hitzeschild und dichtungInfo
- Publication number
- EP4058728A1 EP4058728A1 EP20828973.6A EP20828973A EP4058728A1 EP 4058728 A1 EP4058728 A1 EP 4058728A1 EP 20828973 A EP20828973 A EP 20828973A EP 4058728 A1 EP4058728 A1 EP 4058728A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- heat shield
- combustion chamber
- support structure
- stop element
- cross
- 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.)
- Pending
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
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- 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
- F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
-
- 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
-
- 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
- F23R2900/00017—Assembling combustion chamber liners or subparts
Definitions
- the invention relates to a combustion chamber of a gas turbine with a ceramic heat shield, in which a gap is sealed by means of egg ner seal.
- the combustion chamber initially has a support structure which is made from a metallic material.
- the heat shield is arranged on the inner side of the supporting structure, and this usually consists of a ceramic material.
- An exemplary embodiment for this is known from WO 2019/115129 A1.
- the ceramic heat shield has a significantly higher temperature resistance than the supporting structure.
- the ceramic heat shield serves as insulation between the combustion chamber and the supporting structure.
- the ceramic material of the heat shield in contrast to the support structure, has a significantly greater sensitivity to vibrations or other mechanical loads. It is therefore generally necessary to install the heat shield with as little tension as possible. This usually leads to the presence of gaps both between individual parts of the heat shield and in particular between the heat shield and adjacent components.
- the prior art has borrowed to provide a flow of cooling air that prevents the penetration of hot gas into the gap.
- the object of the present invention is therefore to propose a possibility for reducing the cooling air flow.
- the generic combustion chamber can be provided for different uses, this embodiment being particularly suitable for a gas turbine.
- the combustion chamber defines an approximately centrally located combustion chamber axis which extends from an upstream side to a downstream side.
- the combustion chamber has a supporting structure that encircles the combustion chamber axis.
- the supporting structure consists at least for the most part of a metallic material. Apart from coatings or attachments, the support structure is preferably made of a metallic material.
- the support structure has a reduced cross-section on the downstream side. The way in which the cross-section is reduced is initially irrelevant. On the opposite, upstream side, the support structure forms a stop element. Likewise, the design of the stop element is initially irrelevant.
- a heat shield which - apart from possible fastening means and / or coatings and / or internal reinforcements - consists of a ceramic mate rial. It is provided that the position of the heat shield within the support structure along the combustion chamber axis is limited on the downstream side by the cross-section and on the upstream side by the stop element. To avoid inadmissible clamping of the heat shield in the direction of the combustion chamber between the cross-sectional reduction and the stop element, provision is also made for a gap to exist at least between the heat shield and the stop element.
- the invention provides that a sealing groove extending around the combustion chamber axis and opening towards the heat shield is provided in the stop element.
- a sealing element is arranged in the sealing groove, which stretches out of the stop element and thereby covers the gap and rests on the heat shield.
- the design of the combustion chamber proves to be particularly advantageous if the support structure and consequently the heat shield have a tubular (not necessarily circular) shape.
- At least one spring element is present in the stop element, which is elastically pretensioned together and acts on the sealing element in the direction of the combustion chamber axis, thus ensuring that the sealing element rests reliably on the heat shield is performed. It is particularly advantageous here to use a spring element, which is also arranged in the sealing groove between the groove base and the sealing element.
- the spring element can, for example, have a wave-like shape.
- the cross-sectional reduction on the one hand to map the desired cross-section of the combustion chamber in the downstream area and on the other hand to limit a displacement of the heat shield along the combustion chamber axis can be mapped in different ways.
- the cross-sectional reduction is formed by a conical section.
- the conical shape in this sense does not necessarily require a rotational shape, but similar shapes, which become smaller in cross section downstream, are also included. In an example of a rotational shape, this leads to a reduction in the diameter in the direction of flow of the hot gas in the combustion chamber.
- the heat shield is supported over a section from the outer circumference of the heat shield directly (an outer surface of the heat shield rests on the supporting structure) or particularly advantageously indirectly on the cross-sectional reduction.
- at least one wear protection element and / or elastic tensioning elements are arranged between the outer circumference of the heat shield and the support structure.
- the cross-sectional reduction includes a paragraph.
- the heat shield rests directly or indirectly on the shoulder via an edge section. Adjacent surfaces of the paragraph zes and the adjacent edge portion aligned approximately perpendicular to the combustion chamber axis.
- the defined support in the direction of the combustion chamber axis is advantageous, with the disadvantage of the possibly more complex design of the support structure and the heat shield. In this case it is irrelevant whether the cross-sectional reduction continues to have a conical shape.
- the heat shield can be formed by a single heat shield element.
- the heat shield is advantageously formed in the direction of the combustion chamber axis by at least two heat shield elements.
- the at least two successive heat shield elements bear directly or indirectly on one another (for example with an intermediate wear protection device).
- the heat shield is formed in the circumferential direction by at least two heat shield elements.
- these rest directly or indirectly against one another.
- At least one tensioning element acting in the radial direction is present between the heat shield and the support structure.
- the several distributed in the circumference Spannele elements which together cause the central positioning of the heat shield. This ensures tolerance compensation and compensation for thermal expansions.
- Blattfe countries are preferably used as clamping elements.
- the combustion chamber 01 defines a combustion chamber axis and initially comprises a rotationally shaped supporting structure 02.
- This 02 has a cross-sectional reduction 03 with a conical shape on the downstream side.
- a stop element 04 in the form of a shoulder.
- the heat shield 11 is formed in this example by three heat shield elements 12, 13.
- the heat shield element 12 arranged downstream like the cross-sectional reduction 03, has a conical shape.
- the outer circumference of the heat shield element 12 rests against the inside of the cross-sectional reduction 03.
- tensioning elements are present between the heat shield 11 and the support structure 02 in the area of the cross-sectional reduction 03.
- direct contact of the heat shield element 12 on the support structure 02 is avoided and at the same time the central position is ensured even with slight differences in shape between the heat shield 12 and the support structure 02.
- the position of the heat shield 11 is thus limited in the downstream direction.
- the heat shield 11 Adjacent to this on the upstream side, the heat shield 11 is formed by two heat shield elements 13 subdivided in the circumferential direction. To ensure a central position, it is provided here at that several clamping elements 14 acting in the radial direction are arranged between the heat shield elements 13 and the support structure 02, distributed around the circumference.
- sealing groove 05 with the sealing element 06 arranged therein can also be seen.
- the sealing element 06 rests against the heat shield elements 13 and covers a gap between the heat shield 11 and the stop 04. This avoids unnecessary cooling air consumption.
- an elastically prestressed spring element 07 is also provided, which 07 is arranged in the sealing groove 05 between the groove base and the sealing element 06.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102020203017.0A DE102020203017A1 (de) | 2020-03-10 | 2020-03-10 | Brennkammer mit keramischem Hitzeschild und Dichtung |
PCT/EP2020/085430 WO2021180349A1 (de) | 2020-03-10 | 2020-12-10 | Brennkammer mit keramischem hitzeschild und dichtung |
Publications (1)
Publication Number | Publication Date |
---|---|
EP4058728A1 true EP4058728A1 (de) | 2022-09-21 |
Family
ID=74003805
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20828973.6A Pending EP4058728A1 (de) | 2020-03-10 | 2020-12-10 | Brennkammer mit keramischem hitzeschild und dichtung |
Country Status (6)
Country | Link |
---|---|
US (1) | US20230130521A1 (zh) |
EP (1) | EP4058728A1 (zh) |
KR (1) | KR20220149747A (zh) |
CN (1) | CN115298485B (zh) |
DE (1) | DE102020203017A1 (zh) |
WO (1) | WO2021180349A1 (zh) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN116379474B (zh) * | 2023-02-22 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | 一种航空发动机燃油喷嘴热防护结构 |
Family Cites Families (34)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH633351A5 (de) * | 1978-11-09 | 1982-11-30 | Sulzer Ag | Waermedehnungen nachgebende abdichtung einer ringbrennkammer fuer eine gasturbine. |
DE50310313D1 (de) * | 2003-01-29 | 2008-09-25 | Siemens Ag | Brennkammer |
EP1561997A1 (de) * | 2004-01-27 | 2005-08-10 | Siemens Aktiengesellschaft | Hitzeschild |
US8695989B2 (en) * | 2004-04-30 | 2014-04-15 | Siemens Aktiengesellschaft | Hot gas seal |
ES2296165T3 (es) * | 2004-05-05 | 2008-04-16 | Alstom Technology Ltd | Camara de combustion para turbina de gas. |
US7007482B2 (en) * | 2004-05-28 | 2006-03-07 | Power Systems Mfg., Llc | Combustion liner seal with heat transfer augmentation |
CA2619081C (en) * | 2005-08-23 | 2011-03-22 | Mitsubishi Heavy Industries, Ltd. | Seal structure of gas turbine combustor |
US7546743B2 (en) * | 2005-10-12 | 2009-06-16 | General Electric Company | Bolting configuration for joining ceramic combustor liner to metal mounting attachments |
US20090120093A1 (en) | 2007-09-28 | 2009-05-14 | General Electric Company | Turbulated aft-end liner assembly and cooling method |
US8713945B2 (en) * | 2010-06-29 | 2014-05-06 | Nuovo Pignone S.P.A. | Liner aft end support mechanisms and spring loaded liner stop mechanisms |
FR2989426B1 (fr) * | 2012-04-11 | 2014-03-28 | Snecma | Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion |
EP3044511B1 (en) | 2013-09-11 | 2021-10-06 | Raytheon Technologies Corporation | Combustor, gas turbine engine comprising such a combustor, and method |
EP3017253B1 (de) * | 2013-09-11 | 2017-04-26 | Siemens Aktiengesellschaft | Keramisches hitzeschild für eine gasturbinenbrennkammer, brennkammer für eine gasturbine und verfahren |
DE102013220482B3 (de) | 2013-10-10 | 2015-04-09 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Haltevorrichtung zur wärmeausdehnungskompensierenden, klemmenden Fixierung eines hitzebeständigen Wandelements einer Brennkammer |
DE102014204481A1 (de) * | 2014-03-11 | 2015-09-17 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammer einer Gasturbine |
US9612017B2 (en) * | 2014-06-05 | 2017-04-04 | Rolls-Royce North American Technologies, Inc. | Combustor with tiled liner |
KR102445062B1 (ko) * | 2014-12-15 | 2022-09-21 | 누보 피그노네 테크놀로지 에스알엘 | 연소기 라이너 가요성 지지 및 방법 |
GB201501817D0 (en) * | 2015-02-04 | 2015-03-18 | Rolls Royce Plc | A combustion chamber and a combustion chamber segment |
WO2016167784A1 (en) * | 2015-04-17 | 2016-10-20 | Siemens Aktiengesellschaft | Flexible interface system for a combustor of a gas turbine engine |
US10801729B2 (en) * | 2015-07-06 | 2020-10-13 | General Electric Company | Thermally coupled CMC combustor liner |
US10648669B2 (en) | 2015-08-21 | 2020-05-12 | Rolls-Royce Corporation | Case and liner arrangement for a combustor |
US10197278B2 (en) * | 2015-09-02 | 2019-02-05 | General Electric Company | Combustor assembly for a turbine engine |
US10519794B2 (en) * | 2016-07-12 | 2019-12-31 | General Electric Company | Sealing system for sealing against a non-cylindrical surface |
DE102016222099A1 (de) | 2016-11-10 | 2018-05-17 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammer einer Gasturbine |
WO2018128600A1 (en) * | 2017-01-04 | 2018-07-12 | Siemens Aktiengesellschaft | Side seal for the transition duct system of a gas turbine engine |
GB201700763D0 (en) * | 2017-01-17 | 2017-03-01 | Rolls Royce Plc | Pressure responseive valve for a cooling flow in a gas turbine |
US10801730B2 (en) * | 2017-04-12 | 2020-10-13 | Raytheon Technologies Corporation | Combustor panel mounting systems and methods |
US20180340687A1 (en) * | 2017-05-24 | 2018-11-29 | Siemens Aktiengesellschaft | Refractory ceramic component for a gas turbine engine |
EP3499125A1 (de) | 2017-12-12 | 2019-06-19 | Siemens Aktiengesellschaft | Rohrbrennkammer mit keramischer auskleidung |
FR3081494B1 (fr) * | 2018-05-28 | 2020-12-25 | Safran Aircraft Engines | Module de combustion de turbomachine a gaz avec butee de fond de chambre |
US11339966B2 (en) * | 2018-08-21 | 2022-05-24 | General Electric Company | Flow control wall for heat engine |
US11255547B2 (en) * | 2018-10-15 | 2022-02-22 | Raytheon Technologies Corporation | Combustor liner attachment assembly for gas turbine engine |
US11293637B2 (en) * | 2018-10-15 | 2022-04-05 | Raytheon Technologies Corporation | Combustor liner attachment assembly for gas turbine engine |
US11215367B2 (en) * | 2019-10-03 | 2022-01-04 | Raytheon Technologies Corporation | Mounting a ceramic component to a non-ceramic component in a gas turbine engine |
-
2020
- 2020-03-10 DE DE102020203017.0A patent/DE102020203017A1/de not_active Withdrawn
- 2020-12-10 US US17/802,947 patent/US20230130521A1/en not_active Abandoned
- 2020-12-10 WO PCT/EP2020/085430 patent/WO2021180349A1/de unknown
- 2020-12-10 CN CN202080098356.7A patent/CN115298485B/zh active Active
- 2020-12-10 KR KR1020227034562A patent/KR20220149747A/ko not_active Application Discontinuation
- 2020-12-10 EP EP20828973.6A patent/EP4058728A1/de active Pending
Also Published As
Publication number | Publication date |
---|---|
CN115298485B (zh) | 2023-10-27 |
KR20220149747A (ko) | 2022-11-08 |
US20230130521A1 (en) | 2023-04-27 |
CN115298485A (zh) | 2022-11-04 |
DE102020203017A1 (de) | 2021-09-16 |
WO2021180349A1 (de) | 2021-09-16 |
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