GB787738A - Combustion turbine power units - Google Patents

Combustion turbine power units

Info

Publication number
GB787738A
GB787738A GB10319/55A GB1031955A GB787738A GB 787738 A GB787738 A GB 787738A GB 10319/55 A GB10319/55 A GB 10319/55A GB 1031955 A GB1031955 A GB 1031955A GB 787738 A GB787738 A GB 787738A
Authority
GB
United Kingdom
Prior art keywords
turbine
casing
gear casing
exhaust
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
GB10319/55A
Inventor
Ronald Albert Gilbert
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.)
Napier Turbochargers Ltd
Original Assignee
D Napier and Son Ltd
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 D Napier and Son Ltd filed Critical D Napier and Son Ltd
Publication of GB787738A publication Critical patent/GB787738A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
    • B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Retarders (AREA)
  • Exhaust Silencers (AREA)

Abstract

787,738. Gas turbine plant. NAPIER & SON, Ltd., D. March 23, 1956 [April 7, 1955], No. 10319/55. Class 110 (3). In a gas turbine power plant, the turbine which may be either the turbine driving the compressor or a separate power turbine, is connected through reduction gearing to a power output shaft, the reduction gearing being contained in a casing disposed of the side of the turbine remote from the compressor and comprising an input shaft coaxial with and directly driven by the turbine, the power output shaft projecting from the side of the gear casing remote from the turbine. Exhaust ducting is disposed between the turbine and the reduction gear casing, and the gear casing is supported directly from the turbine casing independently of the exhaust ducting by means of a series of circumferentially-spaced stress - transmitting members. The invention is shown applied to a helicopter, the power unit being mounted vertically and comprising a compressor A<SP>1</SP>, combustion equipment A<SP>2</SP> and turbine A<SP>3</SP>, the turbine driving the compressor A<SP>1</SP> and supplying external power through shaft C<SP>1</SP>. An exhaust duct is connected to the turbine casing A<SP>3</SP> and comprises an annular portion B which diverges to two outwardly-projecting outlets B<SP>2</SP>. The reduction gear casing is shown at C and the lower portion thereof is disposed between the two outlets B<SP>2</SP>. The gear casing is provided with four radially-extending arms D<SP>1</SP> which are pivotally connected to four brackets D which are mounted directly on the flange B<SP>1</SP> of the turbine casing A<SP>3</SP>, two of the arms D<SP>1</SP> extending through the spaces B<SP>6</SP> between the exhaust outlets B<SP>2</SP>, and the other two arms extending through housings B' which pass across the two exhaust outlets. The power unit is supported from the airframe by means of struts G3, G4 which are connected to brackets G<SP>5</SP> on the power unit, the axes of the struts G<SP>3</SP>, G4 intersecting at the centre of gravity H of the power unit. The upper end of the reduction gear casing C is connected by a torque-transmitting coupling C<SP>3</SP> to the helicopter rotor reduction gear casing F which is rigidly connected to the airframe. The two exhaust outlets B<SP>2</SP> are interconnected by members B<SP>5</SP>. The invention is also applicable to gas turbine units driving an aircraft propeller. Specifications 761,442 and 787,739 are referred to.
GB10319/55A 1955-04-07 1955-04-07 Combustion turbine power units Expired GB787738A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB339782X 1955-04-07

Publications (1)

Publication Number Publication Date
GB787738A true GB787738A (en) 1957-12-18

Family

ID=10359813

Family Applications (2)

Application Number Title Priority Date Filing Date
GB10319/55A Expired GB787738A (en) 1955-04-07 1955-04-07 Combustion turbine power units
GB20348/57A Expired GB856347A (en) 1955-04-07 1957-06-27 Combustion turbine power units

Family Applications After (1)

Application Number Title Priority Date Filing Date
GB20348/57A Expired GB856347A (en) 1955-04-07 1957-06-27 Combustion turbine power units

Country Status (4)

Country Link
BE (2) BE546852A (en)
CH (1) CH339782A (en)
GB (2) GB787738A (en)
NL (1) NL100163C (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2956700A1 (en) * 2010-02-25 2011-08-26 Turbomeca TURBOMACHINE WITH VERTICAL SHAFT

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2956700A1 (en) * 2010-02-25 2011-08-26 Turbomeca TURBOMACHINE WITH VERTICAL SHAFT
WO2011104477A1 (en) * 2010-02-25 2011-09-01 Turbomeca Turbomachine comprising a vertical shaft
CN102782261A (en) * 2010-02-25 2012-11-14 涡轮梅坎公司 Turbomachine comprising a vertical shaft
CN102782261B (en) * 2010-02-25 2015-02-18 涡轮梅坎公司 Turbomachine comprising a vertical shaft
US9163526B2 (en) 2010-02-25 2015-10-20 Turbomeca Vertical shaft turbomachine
RU2566869C2 (en) * 2010-02-25 2015-10-27 Турбомека Turbo machine with vertical rotor

Also Published As

Publication number Publication date
CH339782A (en) 1959-07-15
BE546852A (en)
BE546853A (en)
NL100163C (en)
GB856347A (en) 1960-12-14

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