EP2527743A3 - Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber - Google Patents

Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber Download PDF

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Publication number
EP2527743A3
EP2527743A3 EP12169511.8A EP12169511A EP2527743A3 EP 2527743 A3 EP2527743 A3 EP 2527743A3 EP 12169511 A EP12169511 A EP 12169511A EP 2527743 A3 EP2527743 A3 EP 2527743A3
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
annular combustion
aircraft engine
producing
segment component
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
EP12169511.8A
Other languages
German (de)
French (fr)
Other versions
EP2527743B1 (en
EP2527743A2 (en
Inventor
Karl Schreiber
Miklos Gerendas
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd 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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2527743A2 publication Critical patent/EP2527743A2/en
Publication of EP2527743A3 publication Critical patent/EP2527743A3/en
Application granted granted Critical
Publication of EP2527743B1 publication Critical patent/EP2527743B1/en
Not-in-force 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/4927—Cylinder, cylinder head or engine valve sleeve making

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Laser Beam Processing (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Abstract

Die Erfindung betrifft ein Segmentbauteil aus Hochtemperaturgussmaterial für eine Ringbrennkammer eines Flugzeugtriebwerkes, gekennzeichnet durch eine Brennkammerwand (11, 12), die im Betrieb eine sich entlang einer Brennerachse (21) erstreckende Brennstoffflamme (20) gegenüber der Umgebung abschirmt, wobei die Brennkammerwand (11, 12) eine Ausbuchtung (13, 14) in eine Richtung aufweist, die von der Brennerachse (21) wegzeigt. Die Erfindung betrifft ferner eine Ringbrennkammer, ein Flugzeugtriebwerk mit einer Ringbrennkammer, sowie Verfahren zur Herstellung einer Ringbrennkammer.

Figure imgaf001
The invention relates to a segment component of high-temperature casting material for an annular combustion chamber of an aircraft engine, characterized by a combustion chamber wall (11, 12) which shields a fuel flame (20) extending along a burner axis (21) from the environment during operation, the combustion chamber wall (11, 12) has a bulge (13, 14) in a direction pointing away from the burner axis (21). The invention further relates to an annular combustion chamber, an aircraft engine with an annular combustion chamber, and method for producing an annular combustion chamber.
Figure imgaf001
EP12169511.8A 2011-05-25 2012-05-25 Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber Not-in-force EP2527743B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102011076473A DE102011076473A1 (en) 2011-05-25 2011-05-25 High temperature casting material segment component for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine, and method of manufacturing an annular combustion chamber

Publications (3)

Publication Number Publication Date
EP2527743A2 EP2527743A2 (en) 2012-11-28
EP2527743A3 true EP2527743A3 (en) 2015-01-21
EP2527743B1 EP2527743B1 (en) 2016-09-28

Family

ID=46148713

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12169511.8A Not-in-force EP2527743B1 (en) 2011-05-25 2012-05-25 Segment component comprising high temperature cast material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for producing an annular combustion chamber

Country Status (3)

Country Link
US (1) US8646279B2 (en)
EP (1) EP2527743B1 (en)
DE (1) DE102011076473A1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013222863A1 (en) 2013-11-11 2015-05-13 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustor and method for its production
DE102014204468A1 (en) * 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustor and method for its production
DE102016201452A1 (en) * 2016-02-01 2017-08-03 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustor with wall contouring
CN111059575B (en) * 2018-10-16 2022-05-10 中发天信(北京)航空发动机科技股份有限公司 Turbojet engine flame tube shell
US20200318549A1 (en) * 2019-04-04 2020-10-08 United Technologies Corporation Non-axisymmetric combustor for improved durability
GB202019222D0 (en) 2020-12-07 2021-01-20 Rolls Royce Plc Lean burn combustor
GB202019219D0 (en) * 2020-12-07 2021-01-20 Rolls Royce Plc Lean burn combustor
US11940151B2 (en) 2022-01-12 2024-03-26 General Electric Company Combustor with baffle

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1106927A1 (en) * 1999-12-09 2001-06-13 Rolls-Royce Deutschland Ltd & Co KG Method of manufacturing a gas turbine engine combustion chamber
EP1584871A2 (en) * 2004-04-08 2005-10-12 United Technologies Corporation Single crystal articles having controlled crystallographic orientation
EP1760402A2 (en) * 2005-08-30 2007-03-07 United Technologies Corporation Method for casting cooling holes
US20070062198A1 (en) * 2003-05-30 2007-03-22 Siemens Aktiengesellschaft Combustion chamber

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB741836A (en) * 1953-03-05 1955-12-14 Lucas Industries Ltd Combustion chambers for jet-propulsion engines, gas turbines or other prime movers
CA2056592A1 (en) * 1990-12-21 1992-06-22 Phillip D. Napoli Multi-hole film cooled combustor liner with slotted film starter
US5964091A (en) * 1995-07-11 1999-10-12 Hitachi, Ltd. Gas turbine combustor and gas turbine
EP1312865A1 (en) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Gas turbine annular combustion chamber
DE50212643D1 (en) 2002-11-22 2008-09-25 Siemens Ag Combustion chamber for combustion of a combustible fluid mixture
GB2420614B (en) * 2004-11-30 2009-06-03 Alstom Technology Ltd Tile and exo-skeleton tile structure
US7540156B2 (en) * 2005-11-21 2009-06-02 General Electric Company Combustion liner for gas turbine formed of cast nickel-based superalloy
EP2100687A1 (en) * 2008-02-29 2009-09-16 Siemens Aktiengesellschaft Potential-free wire heating during welding and device for this purpose

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1106927A1 (en) * 1999-12-09 2001-06-13 Rolls-Royce Deutschland Ltd & Co KG Method of manufacturing a gas turbine engine combustion chamber
US20070062198A1 (en) * 2003-05-30 2007-03-22 Siemens Aktiengesellschaft Combustion chamber
EP1584871A2 (en) * 2004-04-08 2005-10-12 United Technologies Corporation Single crystal articles having controlled crystallographic orientation
EP1760402A2 (en) * 2005-08-30 2007-03-07 United Technologies Corporation Method for casting cooling holes

Also Published As

Publication number Publication date
EP2527743B1 (en) 2016-09-28
US20120304658A1 (en) 2012-12-06
US8646279B2 (en) 2014-02-11
EP2527743A2 (en) 2012-11-28
DE102011076473A1 (en) 2012-11-29

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