FR2274788A1 - Perfectionnement aux installations motrices a turbine a gaz comprenant deux grilles d'aubes superposees - Google Patents

Perfectionnement aux installations motrices a turbine a gaz comprenant deux grilles d'aubes superposees

Info

Publication number
FR2274788A1
FR2274788A1 FR7420729A FR7420729A FR2274788A1 FR 2274788 A1 FR2274788 A1 FR 2274788A1 FR 7420729 A FR7420729 A FR 7420729A FR 7420729 A FR7420729 A FR 7420729A FR 2274788 A1 FR2274788 A1 FR 2274788A1
Authority
FR
France
Prior art keywords
compressor
superimposed
rings
ring
gas turbine
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
FR7420729A
Other languages
English (en)
French (fr)
Other versions
FR2274788B1 (enExample
Inventor
Serge Boudigues
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR7420729A priority Critical patent/FR2274788A1/fr
Publication of FR2274788A1 publication Critical patent/FR2274788A1/fr
Application granted granted Critical
Publication of FR2274788B1 publication Critical patent/FR2274788B1/fr
Granted legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR7420729A 1974-06-14 1974-06-14 Perfectionnement aux installations motrices a turbine a gaz comprenant deux grilles d'aubes superposees Granted FR2274788A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR7420729A FR2274788A1 (fr) 1974-06-14 1974-06-14 Perfectionnement aux installations motrices a turbine a gaz comprenant deux grilles d'aubes superposees

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7420729A FR2274788A1 (fr) 1974-06-14 1974-06-14 Perfectionnement aux installations motrices a turbine a gaz comprenant deux grilles d'aubes superposees

Publications (2)

Publication Number Publication Date
FR2274788A1 true FR2274788A1 (fr) 1976-01-09
FR2274788B1 FR2274788B1 (enExample) 1977-10-07

Family

ID=9140080

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7420729A Granted FR2274788A1 (fr) 1974-06-14 1974-06-14 Perfectionnement aux installations motrices a turbine a gaz comprenant deux grilles d'aubes superposees

Country Status (1)

Country Link
FR (1) FR2274788A1 (enExample)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006059989A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006059978A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Cantilevered tip turbine engine
WO2006059970A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
WO2006060004A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Combustor for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
WO2006059985A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Axial compressor for tip turbine engine
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
WO2006059986A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
WO2006059971A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
WO2006059988A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
EP1831530B1 (en) 2004-12-01 2009-02-25 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
EP2333286A1 (en) 2004-12-01 2011-06-15 United Technologies Corporation Vectoring transition duct for turbine engine
WO2006060000A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006059989A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US10760483B2 (en) 2004-12-01 2020-09-01 Raytheon Technologies Corporation Tip turbine engine composite tailcone

Also Published As

Publication number Publication date
FR2274788B1 (enExample) 1977-10-07

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Legal Events

Date Code Title Description
ST Notification of lapse