EP1577614A1 - Bouclier thermique - Google Patents

Bouclier thermique Download PDF

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Publication number
EP1577614A1
EP1577614A1 EP04006582A EP04006582A EP1577614A1 EP 1577614 A1 EP1577614 A1 EP 1577614A1 EP 04006582 A EP04006582 A EP 04006582A EP 04006582 A EP04006582 A EP 04006582A EP 1577614 A1 EP1577614 A1 EP 1577614A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
profile
support structure
hot medium
groove
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
EP04006582A
Other languages
German (de)
English (en)
Other versions
EP1577614B1 (fr
Inventor
Beate Seiler
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
Priority to EP04006582.3A priority Critical patent/EP1577614B1/fr
Publication of EP1577614A1 publication Critical patent/EP1577614A1/fr
Application granted granted Critical
Publication of EP1577614B1 publication Critical patent/EP1577614B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/42—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
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/04—Supports for linings
    • 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

Definitions

  • the present invention relates to a heat shield on a Support structure for protecting the support structure and / or a Support structure comprehensive or connected to the support structure Wall against flowing hot gas, which number of The support structure of attached heat shield elements comprises, a Support structure for holding heat shield elements and a Heat shield element.
  • heat shields are used.
  • They are thermal highly loaded combustion chambers of gas turbines for protection the combustion chambers from excessive thermal stress with a heat shield lined.
  • the heat shield typically includes a number of surface arranged metallic or ceramic heat shield elements (hereinafter merely referred to as heat shield elements), that of a in the combustion chamber wall formed, usually metallic Support structure are kept.
  • the heat shield elements point one of the support structure facing cold side and a hot Medium facing hot side and shield the wall the combustion chamber and the supporting structure against the hot medium, about a hot combustion gas, making it an excessive thermal load of the combustion chamber wall and the Counteract support structure.
  • the grooves in the supporting structure inserted element holders are usually bolted to the support structure.
  • the element holders include in addition to the section for insertion into the grooves Head part, which in the groove of a hot side with the Cold side connecting circumferential surface of the heat shield element engages to fix it to the support structure.
  • the heat shield elements are arranged side by side under Spaltbemik comprehensive, ie between their peripheral surfaces are gaps in which the hot medium can penetrate.
  • the hot medium can reach the element holders. Since the metallic element holders would scale or melt at the temperatures prevailing in the combustion chamber, they are cooled by means of cooling air which flows through holes in the support structure into the gaps. This cooling air is taken from the compressor end of the gas turbine and is therefore no longer available to the combustion process, which leads to an increase in the NO x emission.
  • Another object of the present invention is to suitable heat shield element for the heat shield according to the invention to provide.
  • the first object is achieved by a heat shield according to claim 1, the second object by a heat shield element according to claim 6 and the third object by a support structure according to claim 11 solved.
  • the dependent claims contain advantageous Embodiments of the present invention.
  • a hot gas comprises a number on the support structure fortified heat shield elements, which, for example, from a be made of ceramic or a metallic material can.
  • the heat shield elements are inventively means a positive connection fixed to the support structure.
  • the connection between the heat shield element and support structure is achieved by positive locking, no metallic holding elements are more necessary, which would have to be cooled by means of cooling air.
  • a saving of cooling air and thereby a reduction of NO x emission is possible.
  • ceramic heat shields can endure the temperatures prevailing in the gas turbine combustors uncooled.
  • material can be saved since both the element holders and the fastening screws for fastening the element holders to the fastening structure are no longer needed.
  • heat shield elements in particular ceramic heat shield elements can be poured frequently, the shape of the supporting structure facing cold side of ceramic heat shield elements be chosen relatively freely, so they are so that they can be designed together with a corresponding one Shaping the support structure a good fit allows.
  • the inventive positive fastening of the heat shield elements on the support structure faces the stand
  • the technology is a completely different attachment principle.
  • the heat shield elements at their the support structure to be turned Cold side in each case at least one profile foot with Profile surfaces, wherein the profile surfaces first active surfaces represent for the form-liquid compound.
  • the support structure has at least one profile groove with profile surfaces, the second active surfaces for the positive connection represent and together with the profile surfaces of the Profile foot, so together with the first active surfaces, effective area pairs form for the positive connection.
  • heat shield elements in particular ceramic heat shield elements, as mentioned above, are usually poured the shape of the profile foot can be chosen relatively freely. This makes it possible for the profile foot and the profile groove to choose relatively simple shapes. This can help with the Production of heat shields achieved significant savings become, because otherwise in the state of the art no longer two complex formed grooves are introduced into the support structure but a wide, simpler shaped groove is sufficient. In addition, all cooling air holes as well all fixing holes for fixing the element holder to be omitted on the support structure.
  • the heat shield according to the invention extend the profile surfaces of the profile perpendicular to Flow direction of the hot medium, i. perpendicular to the axial direction the gas turbine. The same applies to the with the profile surfaces of the profile groove cooperating profile surfaces the profile feet of the heat shield elements. The heat shield elements are then against displacements in the axial direction secured the gas turbine.
  • Heat shields are the active surfaces of the heat shield elements and / or the at least one profile groove with a friction-reducing Coating provided so that the heat shield elements after inserting the profile foot into the profile groove easier to move along the groove. Thereby can be moved and thus placing the heat shield elements in the groove when building the heat shield easier.
  • a heat-resistant material is particularly suitable Teflon as the material for the friction-reducing coating.
  • a heat shield element according to the invention which in particular suitable for building a heat shield according to the invention is, has a cold side, the one of the heat shield element is to turn holding support structure.
  • the heat shield element also has cold side at least one profile foot with profile surfaces, which first active surfaces for a form-fitting Represent connection with the support structure.
  • Such a heat shield element is suitable for positive locking Connecting with a suitably formed support structure.
  • the profile surfaces can be arranged on the profile foot be that they attach to the appropriate after attaching Support structure perpendicular to the flow direction of the hot medium, i. perpendicular to the axial direction of the gas turbine, extend.
  • the profile foot of the heat shield element according to the invention may in particular be designed in such a way that peripheral surfaces of the heat shield element, which the Connect cold side with a hot side and after fixing on the support structure perpendicular to the flow direction extend the hot gas, have recesses or grooves, which the heat shield element in an actual shield part and divide the tread foot.
  • the actual shield part of the heat shield element can in particular in comparison unchanged to heat shield elements according to the prior art be educated.
  • the heat shield element in the profile groove too It can be a friction-reducing coating have, in particular formed as a Teflon coating can be.
  • a support structure according to the invention for a heat shield for Holding heat shield elements on one against a hot medium wall to be protected comprises a profile groove, which profile surfaces has, the active surfaces for a positive Includes connection with the heat shield elements.
  • the inventive Support structure allows, together with suitable Heat shield elements a heat shield according to the invention build.
  • the profile can perpendicular to the flow direction of the hot medium, i. perpendicular to Axial direction of the gas turbine, so that on the support structure to be fastened heat shield elements in the axial direction of Gas turbine are secured.
  • the profile surfaces of the support structure according to the invention can have a friction-reducing coating to place to simplify the heat shield elements in the profile groove.
  • the friction-reducing coating can in particular be a Teflon coating.
  • each profile groove at least one threading point for insertion of profile feet of heat shield elements in the respective Profile groove.
  • Fig. 1 shows a ceramic heat shield element according to the invention in a perspective view.
  • Fig. 2 shows a section of a support structure according to the invention in a perspective view.
  • Fig. 3 shows the positive connection of a ceramic Heat shield element with the support structure in a cut Side view.
  • FIG. 1 shows a ceramic heat shield element according to the invention for a hot gas leading combustion chamber of a gas turbine in a perspective view.
  • the heat shield element 10 includes a hot gas in the gas turbine combustor hot side facing 12, one of the heat shield element 10 holding support structure zuaddde cold side 14 and the Cold side 14 with the hot side 12 connecting peripheral sides or peripheral surfaces 16, 18.
  • Two of the peripheral surfaces, namely the peripheral surfaces 16 extend into the gas turbine combustor installed state of the heat shield element 10 perpendicular to the axial direction of the gas turbine combustor and thus perpendicular to the flow direction of the hot gas.
  • the two other peripheral sides 18, however, extend in the axial direction the gas turbine combustor, i. parallel to Flow direction of the hot gas.
  • In the built-in Condition perpendicular to the axial direction of the gas turbine extending Circumferential surfaces 16 are recesses or grooves 20 present which the heat shield element 10 in a proper Shield part 22 and a profile foot 24 divide.
  • the profile foot 24 is used to attach the heat shield element 10 in a profile groove 52 of a support structure 50 (see FIG 2).
  • the profile foot 24 has beveled surfaces 26, the active surfaces for producing a positive connection represent with the profile groove 52 of the support structure 50.
  • active surfaces 54 In the profiled groove 52 are also formed active surfaces 54, the complementary to the active surfaces 26 of the profile foot 24th are formed and in interaction with these the positive connection manufacture, which is the ceramic heat shield element in the groove 52 stops.
  • the profile edges compared to the profile edges 58, 59 of the profile groove 52 a greater distance from each other have, so the width of the profile groove 52 in the area the threading point 60 is increased, and that much that the profile foot 24 of the heat shield element 10 in the profile 52 can be used.
  • From the threading point 60 from the heat shield element 10 then to its destination within shifted the profile groove 52.
  • the profile surfaces 26 of the profile foot 24 or the profile surfaces 54 of the Profilnut 52 with a sliding friction-reducing coating be provided.
  • As material for the coating offers Teflon due to its high temperature resistance at.
  • both the profile surfaces 54 of the profile groove 52 and the profile surfaces 26 of the profile foot 24 provided with the friction-reducing coating be.

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)
EP04006582.3A 2004-03-18 2004-03-18 Arrangement d'une structure de support et d'un bouclier thermique d'un turbine à gaz Expired - Lifetime EP1577614B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04006582.3A EP1577614B1 (fr) 2004-03-18 2004-03-18 Arrangement d'une structure de support et d'un bouclier thermique d'un turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04006582.3A EP1577614B1 (fr) 2004-03-18 2004-03-18 Arrangement d'une structure de support et d'un bouclier thermique d'un turbine à gaz

Publications (2)

Publication Number Publication Date
EP1577614A1 true EP1577614A1 (fr) 2005-09-21
EP1577614B1 EP1577614B1 (fr) 2013-12-04

Family

ID=34833646

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04006582.3A Expired - Lifetime EP1577614B1 (fr) 2004-03-18 2004-03-18 Arrangement d'une structure de support et d'un bouclier thermique d'un turbine à gaz

Country Status (1)

Country Link
EP (1) EP1577614B1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1617146A3 (fr) * 2004-07-12 2009-05-06 United Technologies Corporation Composant de bouclier thermique
EP2216601A3 (fr) * 2009-02-06 2017-10-25 General Electric Company Profilé de fixation

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB336520A (en) * 1930-01-28 1930-10-16 Henry Wilmot Spencer Improvements in linings for furnace arches, walls and the like
DE829531C (de) * 1949-09-02 1952-01-28 Maschf Augsburg Nuernberg Ag Temperaturunabhaengige Verbindung von keramischen und metallischen Maschinenteilen
DE2362633A1 (de) * 1973-12-17 1975-06-19 Lucas Aerospace Ltd Flammrohr fuer gasturbinen-triebwerke
JPS594824A (ja) * 1982-06-29 1984-01-11 Toshiba Corp 高温ガスタ−ビン燃焼器構造体
EP0558540A1 (fr) 1990-11-29 1993-09-08 Siemens Ag Ecran thermique en ceramique monte sur une structure portante.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB336520A (en) * 1930-01-28 1930-10-16 Henry Wilmot Spencer Improvements in linings for furnace arches, walls and the like
DE829531C (de) * 1949-09-02 1952-01-28 Maschf Augsburg Nuernberg Ag Temperaturunabhaengige Verbindung von keramischen und metallischen Maschinenteilen
DE2362633A1 (de) * 1973-12-17 1975-06-19 Lucas Aerospace Ltd Flammrohr fuer gasturbinen-triebwerke
JPS594824A (ja) * 1982-06-29 1984-01-11 Toshiba Corp 高温ガスタ−ビン燃焼器構造体
EP0558540A1 (fr) 1990-11-29 1993-09-08 Siemens Ag Ecran thermique en ceramique monte sur une structure portante.

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 0080, no. 87 (M - 291) 20 April 1984 (1984-04-20) *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1617146A3 (fr) * 2004-07-12 2009-05-06 United Technologies Corporation Composant de bouclier thermique
EP2216601A3 (fr) * 2009-02-06 2017-10-25 General Electric Company Profilé de fixation

Also Published As

Publication number Publication date
EP1577614B1 (fr) 2013-12-04

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