GB1277980A - Gas turbine engines - Google Patents

Gas turbine engines

Info

Publication number
GB1277980A
GB1277980A GB43662/70A GB4366270A GB1277980A GB 1277980 A GB1277980 A GB 1277980A GB 43662/70 A GB43662/70 A GB 43662/70A GB 4366270 A GB4366270 A GB 4366270A GB 1277980 A GB1277980 A GB 1277980A
Authority
GB
United Kingdom
Prior art keywords
air
combustion chamber
secondary air
ring valve
controlled
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
GB43662/70A
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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
Priority claimed from DE19691945921 external-priority patent/DE1945921A1/en
Priority claimed from DE19702020416 external-priority patent/DE2020416A1/en
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of GB1277980A publication Critical patent/GB1277980A/en
Expired 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/02—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/40—Movement of component
    • F05B2250/41—Movement of component with one degree of freedom
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/40—Movement of component
    • F05B2250/41—Movement of component with one degree of freedom
    • F05B2250/411—Movement of component with one degree of freedom in rotation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2235/00—Valves, nozzles or pumps
    • F23N2235/02—Air or combustion gas valves or dampers
    • F23N2235/06—Air or combustion gas valves or dampers at the air intake

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

1277980 Gas turbine plant-combustion equipment MOTOREN-UND TURBINEN-UNION MUNCHEN GmbH 11 Sept 1970 [11 Sept 1969 27 April 1970) 43662/70 Heading F1L In a gas turbine engine having means for prelecting air supplied to the combustion chamber, the combustion chamber comprises a flame tube having a plurality of ports for entry of secondary air and means movable to reduce or increase the flow of secondary air through these ports. In the engine shown in Fig. 1 air from the compressor 40 is pre-heated in heat exchanger 42 and passed through line 43 to the combustion chamber which comprises an outer casing 1 and an inner flame tube 2, the flame tube being formed with openings 7 for inflow of primary air and openings 8, 9 for inflow of secondary air. An axially-movable ring valve 10 is disposed around the flame tube being shown in the position in which it closes the secondary air openings 9. The position of the ring valve is controlled in dependence on temperature of air entering the combustion chamber, the temperature being sensed by the device 21 and the signal produced acting through the actuator 23 and rod 12 to position the ring valve. Alternatively the ratio of or the difference between the air preheater inlet temperature and the combustion chamber inlet temperature may be used as the control parameter. In a second embodiment the ring valve 10 is movable circumferentially to control two sets of secondary air openings 8, 9. The ring valve is controlled in dependence on compressor discharge pressure. In Fig. 4 (not shown) a temperature sensing element is mounted in the actuating rod 12 within the air jacket space of the combustion chamber. In Fig. 5 air-flow through opening 37 to the secondary air inlets 34, 35 is controlled by a bi-metallic valve member 38. In Fig.6 (not shown) air-flow in an annular space around the outer wall of the flame tube is controlled by an axially movable ring valve; thus air-flow to the secondary air openings is controlled.
GB43662/70A 1969-09-11 1970-09-11 Gas turbine engines Expired GB1277980A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19691945921 DE1945921A1 (en) 1969-09-11 1969-09-11 Combustion chamber
DE19702020416 DE2020416A1 (en) 1970-04-27 1970-04-27 Combustion chamber for gas turbine engines

Publications (1)

Publication Number Publication Date
GB1277980A true GB1277980A (en) 1972-06-14

Family

ID=25757886

Family Applications (1)

Application Number Title Priority Date Filing Date
GB43662/70A Expired GB1277980A (en) 1969-09-11 1970-09-11 Gas turbine engines

Country Status (1)

Country Link
GB (1) GB1277980A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5317863A (en) * 1992-05-06 1994-06-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine combustion chamber with adjustable primary oxidizer intake passageways

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5317863A (en) * 1992-05-06 1994-06-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Gas turbine combustion chamber with adjustable primary oxidizer intake passageways

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee