FR2312653A2 - Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion - Google Patents

Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion

Info

Publication number
FR2312653A2
FR2312653A2 FR7516967A FR7516967A FR2312653A2 FR 2312653 A2 FR2312653 A2 FR 2312653A2 FR 7516967 A FR7516967 A FR 7516967A FR 7516967 A FR7516967 A FR 7516967A FR 2312653 A2 FR2312653 A2 FR 2312653A2
Authority
FR
France
Prior art keywords
combustion chamber
gas turbine
fuel
radial vanes
holes
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
FR7516967A
Other languages
French (fr)
Other versions
FR2312653B2 (en
Inventor
Jacques Emile Jules Caruel
Philippe Marc Denis Gastebois
Herve Alain Quillevere
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 FR7516967A priority Critical patent/FR2312653A2/en
Publication of FR2312653A2 publication Critical patent/FR2312653A2/en
Application granted granted Critical
Publication of FR2312653B2 publication Critical patent/FR2312653B2/fr
Granted legal-status Critical Current

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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones

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)

Abstract

A gas turbine has a combustion chamber (1) where air from the compressor enters the inlet (2) as in the main patent. Some of this air flows into the inner combustion chamber (4) where fuel supplied through the pipe (11) is burnt. Most of the remaining air stream flows into the annular combustion chamber surrounding the inner chamber (4). Additional fuel is supplied through the pipes (37, 38) then flows out through a number of small holes in radial vanes (30, 31). The fuel jets (45) so formed are then deflected by baffles (46, 47) into the main combustion chamber (9). The thorough mixing of air and fuel due to the turbulence induced by the fuel jets and baffles increases the efficiency of combustion.
FR7516967A 1975-05-30 1975-05-30 Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion Granted FR2312653A2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR7516967A FR2312653A2 (en) 1975-05-30 1975-05-30 Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7516967A FR2312653A2 (en) 1975-05-30 1975-05-30 Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion

Publications (2)

Publication Number Publication Date
FR2312653A2 true FR2312653A2 (en) 1976-12-24
FR2312653B2 FR2312653B2 (en) 1979-06-08

Family

ID=9155886

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7516967A Granted FR2312653A2 (en) 1975-05-30 1975-05-30 Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion

Country Status (1)

Country Link
FR (1) FR2312653A2 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2450947A2 (en) * 1979-03-08 1980-10-03 Rolls Royce IMPROVEMENTS ON TURBOMACHINES

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647369A (en) * 1946-09-06 1953-08-04 Leduc Rene Combustion chamber for fluid fuel burning in an air stream of high velocity
FR2112339A1 (en) * 1970-10-26 1972-06-16 United Aircraft Corp

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647369A (en) * 1946-09-06 1953-08-04 Leduc Rene Combustion chamber for fluid fuel burning in an air stream of high velocity
FR2112339A1 (en) * 1970-10-26 1972-06-16 United Aircraft Corp

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2450947A2 (en) * 1979-03-08 1980-10-03 Rolls Royce IMPROVEMENTS ON TURBOMACHINES

Also Published As

Publication number Publication date
FR2312653B2 (en) 1979-06-08

Similar Documents

Publication Publication Date Title
GB1427146A (en) Combustion apparatus for gas turbine engines
GB791232A (en) Improvements in or relating to gas turbine power plants
GB721126A (en) Improvements in or relating to gas burners
GB1414412A (en) Chamber assembly for use in a continuous combustion process
GB1478395A (en) Apparatus for supplying a mixture of fuel and air to a combustion chamber
GB706645A (en) Metallic combustion chamber for producing hot gases, particularly motive gases for gas turbine installations
GB1341223A (en) Combustion apparatus and apparatus for introducing fuel thereto
GB1352369A (en) Gas turbine engine fuel carbureting devices
GB1311630A (en) Gas turbine power plant
GB1475959A (en) Flare stack gas burner
JPS5482522A (en) Exhaust gas diffuser for engine
GB703002A (en) Improvements in or relating to gas turbines
GB970189A (en) Combustion equipment for a gas turbine engine
GB809300A (en) Improvements relating to combustion chambers for combustion turbines, jet propulsionengines and the like
GB904142A (en) Improvements in or relating to gas-turbine engines
GB627644A (en) Improvements relating to gas-turbine-engines and combustion-equipment therefor
GB619251A (en) Improvements relating to combustion-equipment
FR2312653A2 (en) Secondary combustion chamber for gas turbine - has additional fuel supplied through holes in radial vanes for improved combustion
GB1435820A (en) Gas turbine combustion apparatus liner
GB640104A (en) Improvements in or relating to centrifugal separators
GB1354333A (en) Regenerative gas turbine engines
GB1305887A (en)
GB1397296A (en) Combustion apparatus especially for gas turbine engines
GB1516177A (en) Fuel combustion apparatus
GB809514A (en) Improvements in or relating to combustion chambers