GB1503394A - Metal ceramic structure - Google Patents
Metal ceramic structureInfo
- 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
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.
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)
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 |
-
1976
- 1976-07-01 GB GB2820375A patent/GB1503394A/en not_active Expired
Cited By (29)
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 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PCNP | Patent ceased through non-payment of renewal fee |