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GB1185230A - Improvements in or relating to Gas Turbine Engines - Google Patents

Improvements in or relating to Gas Turbine Engines

Info

Publication number
GB1185230A
GB1185230A GB06026/67A GB1602667A GB1185230A GB 1185230 A GB1185230 A GB 1185230A GB 06026/67 A GB06026/67 A GB 06026/67A GB 1602667 A GB1602667 A GB 1602667A GB 1185230 A GB1185230 A GB 1185230A
Authority
GB
United Kingdom
Prior art keywords
combustion
turbine
shaft
chambers
compressor
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
GB06026/67A
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.)
SABURO YUI
Original Assignee
SABURO YUI
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 SABURO YUI filed Critical SABURO YUI
Publication of GB1185230A publication Critical patent/GB1185230A/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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant

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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

1,185,230. Gas turbine engines; combustion chambers. S. ONISHI and S. YUI. April 7, 1967 [July 2, 1966], No.16026/67. Headings F1G and F1L. A gas turbine engine comprises a compressor, combustion equipment and a turbine which components are constituted by a rotary assembly. In the embodiment shown the compressor is of the centrifugal type and comprises an impeller 1<SP>1</SP> mounted on a shaft 7 and the impeller is connected to the turbine rotor 3<SP>1</SP> by a hollow shaft 7<SP>1</SP> , the combustion chamber assembly 2 being secured to the shaft 71 so as to rotate therewith. The turbine rotor is provided with blades 3<SP>11</SP>. The rotary assembly is mounted within a stator casing 6 and is supported therefrom by means of bearings 24. The object of the invention is to dispense with the diffuser section at the compressor outlet also with the inlet nozzle assembly at the turbine inlet. Fuel is supplied to the combustion section through a duct 11 in the shaft 7 and thence through injectors 12. Sparking plugs 13 are provided adjacent the injectors 12 and are energized at starting. The walls of the combustion section are formed with openings for inflow of air. The turbine blades are provided with longitudinal bores for flow of cooling air, which enters through an axial bore 18 at the radially inner end of the blade. The combustion chamber is divided by partitions into a primary combustion zone 2<SP>1</SP> into which the fuel is delivered and a secondary combustion zone comprising a plurality of chambers 2<SP>11</SP>. The partitions are provided with openings by which the chambers are inter-connected. Air enters the combustion zones through orifices 9 in the wall of the chamber.
GB06026/67A 1966-07-02 1967-04-07 Improvements in or relating to Gas Turbine Engines Expired GB1185230A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP4310766 1966-07-02

Publications (1)

Publication Number Publication Date
GB1185230A true GB1185230A (en) 1970-03-25

Family

ID=12654597

Family Applications (1)

Application Number Title Priority Date Filing Date
GB06026/67A Expired GB1185230A (en) 1966-07-02 1967-04-07 Improvements in or relating to Gas Turbine Engines

Country Status (3)

Country Link
US (1) US3469396A (en)
DE (1) DE1601616A1 (en)
GB (1) GB1185230A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2371595C1 (en) * 2008-02-06 2009-10-27 Олег Васильевич Черемушкин Turbojet engine control device

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4502635A (en) * 1982-09-13 1985-03-05 General Motors Corporation Fuel injection nozzle with auto-rotating tip
US4769996A (en) * 1987-01-27 1988-09-13 Teledyne Industries, Inc. Fuel transfer system for multiple concentric shaft gas turbine engines
US20020152753A1 (en) 1998-09-25 2002-10-24 Anatoly Rakhmailov Fuel mixing in a gas turbine engine
US6557337B1 (en) 1998-09-25 2003-05-06 Alm Development, Inc. Gas turbine engine
US6305157B1 (en) 1998-09-25 2001-10-23 Alm Development, Inc. Gas turbine engine
US6145296A (en) * 1998-09-25 2000-11-14 Alm Development, Inc. Gas turbine engine having counter rotating turbines and a controller for controlling the load driven by one of the turbines
US6212871B1 (en) 1999-03-11 2001-04-10 Alm Development, Inc. Method of operation of a gas turbine engine and a gas turbine engine
US6189311B1 (en) 1999-03-11 2001-02-20 Alm Development, Inc. Gas turbine engine
US6272844B1 (en) 1999-03-11 2001-08-14 Alm Development, Inc. Gas turbine engine having a bladed disk
US6397576B1 (en) 1999-10-12 2002-06-04 Alm Development, Inc. Gas turbine engine with exhaust compressor having outlet tap control
US6363708B1 (en) 1999-10-12 2002-04-02 Alm Development, Inc. Gas turbine engine
US6460324B1 (en) 1999-10-12 2002-10-08 Alm Development, Inc. Gas turbine engine
US6442945B1 (en) 2000-08-04 2002-09-03 Alm Development, Inc. Gas turbine engine
US7047724B2 (en) * 2002-12-30 2006-05-23 United Technologies Corporation Combustion ignition
US6886325B2 (en) * 2002-12-30 2005-05-03 United Technologies Corporation Pulsed combustion engine
WO2005017332A2 (en) * 2003-01-10 2005-02-24 Keogh Rory Rotating combustor gas turbine engine
CN102713203B (en) * 2009-09-13 2015-07-22 贫焰公司 Fuel classification method in combustion equipment
CN115560359B (en) * 2022-09-26 2024-08-27 中国航发湖南动力机械研究所 Swirler assembly and gas turbine combustor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1960810A (en) * 1930-07-26 1934-05-29 Doherty Res Co Gas turbine
US2360130A (en) * 1941-03-26 1944-10-10 Armstrong Siddeley Motors Ltd High-speed propulsion plant
US2404767A (en) * 1941-10-28 1946-07-23 Armstrong Siddeley Motors Ltd Jet propulsion plant
US2736369A (en) * 1953-06-22 1956-02-28 James A Hall Auto-rotative combustion heater
US2836958A (en) * 1954-02-17 1958-06-03 Iii John A Ward Jet power plant with unobstructed rotating combustion chamber
US2951340A (en) * 1956-01-03 1960-09-06 Curtiss Wright Corp Gas turbine with control mechanism for turbine cooling air
US3240012A (en) * 1960-03-16 1966-03-15 Nathan C Price Turbo-jet powerplant

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2371595C1 (en) * 2008-02-06 2009-10-27 Олег Васильевич Черемушкин Turbojet engine control device

Also Published As

Publication number Publication date
DE1601616A1 (en) 1970-08-06
US3469396A (en) 1969-09-30

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLNP Patent lapsed through nonpayment of renewal fees