GB1503394A - Metal ceramic structure - Google Patents

Metal ceramic structure

Info

Publication number
GB1503394A
GB1503394A GB2820375A GB2820375A GB1503394A GB 1503394 A GB1503394 A GB 1503394A GB 2820375 A GB2820375 A GB 2820375A GB 2820375 A GB2820375 A GB 2820375A GB 1503394 A GB1503394 A GB 1503394A
Authority
GB
United Kingdom
Prior art keywords
cone
july
concentric
engine
ceramic structure
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.)
Expired
Application number
GB2820375A
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 PLC
Original Assignee
Rolls Royce PLC
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 PLC filed Critical Rolls Royce PLC
Priority to GB2820375A priority Critical patent/GB1503394A/en
Publication of GB1503394A publication Critical patent/GB1503394A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Exhaust Silencers (AREA)

Abstract

1503394 Jet engines ROLLS-ROYCE (1971) Ltd 1 July 1976 [4 July 1975] 28203/75 Heading F1J A ceramic exhaust cone 18 is supported within the exhaust nozzle 17 of a jet engine by an annular metallic member 19a which is concentric with the low-pressure shaft 19 of the engine and which had splines 20 abutting the ends of ceramic support segments 21 in close fitting relation with the cone 18. This arrangement accommodates differential thermal expansion and contraction of the member 19a and cone 18 while ensuring that these remain concentric.
GB2820375A 1976-07-01 1976-07-01 Metal ceramic structure Expired GB1503394A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2820375A GB1503394A (en) 1976-07-01 1976-07-01 Metal ceramic structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2820375A GB1503394A (en) 1976-07-01 1976-07-01 Metal ceramic structure

Publications (1)

Publication Number Publication Date
GB1503394A true GB1503394A (en) 1978-03-08

Family

ID=10271946

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2820375A Expired GB1503394A (en) 1976-07-01 1976-07-01 Metal ceramic structure

Country Status (1)

Country Link
GB (1) GB1503394A (en)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0080404A1 (en) * 1981-11-19 1983-06-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Assembly of two joined rotationally symmetrical objects made of materials with differing co-efficients of dilatation
EP1069044A2 (en) * 1999-07-15 2001-01-17 The Boeing Company Auxiliary power and thrust unit
WO2006060006A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US9409653B2 (en) 2014-09-17 2016-08-09 The Boeing Company Auxilliary power and thrust unit drive system
EP3708789B1 (en) 2019-03-15 2023-08-16 Hamilton Sundstrand Corporation Integrated tail cone and mounted generator

Cited By (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0080404A1 (en) * 1981-11-19 1983-06-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Assembly of two joined rotationally symmetrical objects made of materials with differing co-efficients of dilatation
US4452038A (en) * 1981-11-19 1984-06-05 S.N.E.C.M.A. System for attaching two rotating parts made of materials having different expansion coefficients
EP1069044A2 (en) * 1999-07-15 2001-01-17 The Boeing Company Auxiliary power and thrust unit
EP1069044A3 (en) * 1999-07-15 2003-11-19 The Boeing Company Auxiliary power and thrust unit
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
WO2006060006A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US8276362B2 (en) 2004-12-01 2012-10-02 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US10760483B2 (en) 2004-12-01 2020-09-01 Raytheon Technologies Corporation Tip turbine engine composite tailcone
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US9409653B2 (en) 2014-09-17 2016-08-09 The Boeing Company Auxilliary power and thrust unit drive system
EP3708789B1 (en) 2019-03-15 2023-08-16 Hamilton Sundstrand Corporation Integrated tail cone and mounted generator

Similar Documents

Publication Publication Date Title
GB1503394A (en) Metal ceramic structure
GB1328993A (en) Air intakes for gas turbine engines
DE3261484D1 (en) Annular combustion chamber with an annular burner for gas turbines
GB2019947B (en) Gas turbine engine combustor assembly
DE3862925D1 (en) INLET PANEL FOR THE COMBUSTION CHAMBER OF A GAS TURBINE.
FR2411968A1 (en) ADVANCED DOUBLE ANNULAR COMBUSTION CHAMBER
JPS53123712A (en) Combined combustor for gas turbine engine with staged injection of preemixed fuel
GB584820A (en) Improvements relating to internal combustion prime movers
NL190855C (en) Combustion chamber for gas turbine engine with cooled jacket.
GB1467301A (en) Catalyst unit for engine exhaust system
IL60648A (en) Gas turbine exhaust thrust vectorable nozzle
GB1549422A (en) Axial flow gas turbine engine compressor
GB1055234A (en) Ultra-high temperature combustion chambers
GB1180706A (en) Flame Tube
GB1524908A (en) Gas turbine engine with anti-icing facility
JPS53122004A (en) Combustion chamber of gas turbine engine
GB2043791B (en) Gas turbine engine rotor thrust compensating
JPS55134213A (en) Gas turbine engine fuel burner
FR2395401A1 (en) COMBUSTION CHAMBER FOR A GAS TURBINE
GB2062839B (en) Gas turbine engine fuel burner
NO874599L (en) PROCEDURE FOR THE PREPARATION OF A COMBUSTION COMBUSTOR FOR ROCKET ENGINE WITH SOLID FUEL.
JPS57198348A (en) Thrust reversal/exhaust gas nozzle assemblage for gas turbine engine
GB1038485A (en) Jet propulsion power plant
GB1059199A (en) Flame tube
SE7607266L (en) GASTURBINE ENGINE

Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee