EP4058728A1 - Chambre de combustion comportant un bouclier thermique et un joint d'étanchéité en céramique - Google Patents

Chambre de combustion comportant un bouclier thermique et un joint d'étanchéité en céramique

Info

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
Application number
EP20828973.6A
Other languages
German (de)
English (en)
Inventor
Matthias Gralki
Claus Krusch
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 Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
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 Energy Global GmbH and Co KG filed Critical Siemens Energy Global GmbH and Co KG
Publication of EP4058728A1 publication Critical patent/EP4058728A1/fr
Pending legal-status Critical Current

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)

Abstract

La présente invention concerne une chambre de combustion (01) d'une turbine à gaz comportant une structure de support périphérique (02) et un bouclier thermique (11) agencé à l'intérieur de celle-ci. La structure de support (02) a une section transversale réduite (03) sur le côté aval et un élément d'arrêt (04) sur le côté amont. Un espacement est situé entre le bouclier thermique (11) et l'élément d'arrêt (04) pour compenser différentes contraintes et tolérances. Afin de réduire la consommation d'air de refroidissement, une rainure d'étanchéité périphérique (05) qui est ouverte vers le bouclier thermique et qui comporte un élément d'étanchéité (06) agencé à l'intérieur de celle-ci (05) est disposée dans l'élément d'arrêt (04), ledit élément d'étanchéité reposant contre le bouclier thermique (11) et recouvrant l'espacement.
EP20828973.6A 2020-03-10 2020-12-10 Chambre de combustion comportant un bouclier thermique et un joint d'étanchéité en céramique Pending EP4058728A1 (fr)

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 (fr) 2020-03-10 2020-12-10 Chambre de combustion comportant un bouclier thermique et un joint d'étanchéité en céramique

Publications (1)

Publication Number Publication Date
EP4058728A1 true EP4058728A1 (fr) 2022-09-21

Family

ID=74003805

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20828973.6A Pending EP4058728A1 (fr) 2020-03-10 2020-12-10 Chambre de combustion comportant un bouclier thermique et un joint d'étanchéité en céramique

Country Status (6)

Country Link
US (1) US20230130521A1 (fr)
EP (1) EP4058728A1 (fr)
KR (1) KR20220149747A (fr)
CN (1) CN115298485B (fr)
DE (1) DE102020203017A1 (fr)
WO (1) WO2021180349A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
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

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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 (fr) 2021-09-16

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