GB1450649A - Premix combustion assembly - Google Patents

Premix combustion assembly

Info

Publication number
GB1450649A
GB1450649A GB822774A GB822774A GB1450649A GB 1450649 A GB1450649 A GB 1450649A GB 822774 A GB822774 A GB 822774A GB 822774 A GB822774 A GB 822774A GB 1450649 A GB1450649 A GB 1450649A
Authority
GB
United Kingdom
Prior art keywords
fuel
air
zone
engine power
power operation
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
GB822774A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB1450649A publication Critical patent/GB1450649A/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Landscapes

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

Abstract

1450649 Gas turbine combustion chambers UNITED AIRCRAFT CORP 22 Feb 1974 [28 Feb 1973] 8227/74 Heading F1L In an annular air-jacketed gas turbine combustion chamber 30, e.g. for jet aircraft a rich mixture of fuel and air is provided in the primary combustion zone 34 for low engine power operation, e.g. for idle or for altitude relight, by conventional fuel nozzles 58 surrounded by swirl vanes 62 and spraying fuel into the zone 34, and a lean mixture of fuel and air is provided in the zone 34 for high engine power operation, e.g. for takeoff, climb and cruise, by injectors 40 having large tangentially directed injection holes 74 arranged in an annular premix passage 42 receiving air from a compressor and delivering the fuel/air mixture through holes 48 in a frusto-conical baffle 46 radially across the zone 34. The baffle may extend from the radially inner, as shown, or outer wall. The holes 48 may be circular, Fig. 2, (not shown), or oval, Fig. 3, (not shown). Local eddies adjacent the holes 48, form a region of stagnant fuel-air mixture which provides a continuous ignition source. The injectors 40 are only operational during high engine power operation, and nozzles 58 may operate continuously or only during low engine power operation.
GB822774A 1973-02-28 1974-02-22 Premix combustion assembly Expired GB1450649A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US33657773A 1973-02-28 1973-02-28

Publications (1)

Publication Number Publication Date
GB1450649A true GB1450649A (en) 1976-09-22

Family

ID=23316720

Family Applications (1)

Application Number Title Priority Date Filing Date
GB822774A Expired GB1450649A (en) 1973-02-28 1974-02-22 Premix combustion assembly

Country Status (5)

Country Link
JP (1) JPS5024618A (en)
CA (1) CA994117A (en)
DE (1) DE2403657A1 (en)
FR (1) FR2219310B1 (en)
GB (1) GB1450649A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2411968A1 (en) * 1977-12-15 1979-07-13 Gen Electric ADVANCED DOUBLE ANNULAR COMBUSTION CHAMBER
GB2269449A (en) * 1992-08-05 1994-02-09 Snecma Combustion chamber with fuel injectors of different types

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3973390A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Combustor employing serially staged pilot combustion, fuel vaporization, and primary combustion zones
GB9201542D0 (en) * 1992-01-24 1992-03-11 Bmw Rolls Royce Gmbh Combustion apparatus for use in a gas turbine
RU2618785C2 (en) * 2011-08-22 2017-05-11 Маджед ТОКАН Tangential and flameless annular combustion chamber for gas turbine engines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2411968A1 (en) * 1977-12-15 1979-07-13 Gen Electric ADVANCED DOUBLE ANNULAR COMBUSTION CHAMBER
GB2269449A (en) * 1992-08-05 1994-02-09 Snecma Combustion chamber with fuel injectors of different types
GB2269449B (en) * 1992-08-05 1995-06-28 Snecma Combustion chamber with fuel injectors of different types

Also Published As

Publication number Publication date
CA994117A (en) 1976-08-03
JPS5024618A (en) 1975-03-15
FR2219310A1 (en) 1974-09-20
DE2403657A1 (en) 1974-09-12
FR2219310B1 (en) 1980-05-23

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Legal Events

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