GB764064A - Gas producers of the gas turbine type - Google Patents

Gas producers of the gas turbine type

Info

Publication number
GB764064A
GB764064A GB13300/53A GB1330053A GB764064A GB 764064 A GB764064 A GB 764064A GB 13300/53 A GB13300/53 A GB 13300/53A GB 1330053 A GB1330053 A GB 1330053A GB 764064 A GB764064 A GB 764064A
Authority
GB
United Kingdom
Prior art keywords
gas
duct
turbine
valve
wall
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
GB13300/53A
Inventor
Alfred John Penn
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
Priority to GB13300/53A priority Critical patent/GB764064A/en
Publication of GB764064A publication Critical patent/GB764064A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F01D25/30—Exhaust heads, chambers, or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)

Abstract

764,064. Jet propelled rotary wing aircraft. NAPIER & SON, Ltd., D. May 4, 1954 [May 12, 1953], No. 13300/53. Class 4. [Also in Group XXVI] A power plant for a helicopter comprises a gas turbine plant, Fig. 1, generating combustion gas which passes by way of a rotary valve 15 as described in Specification 764,063 and a duct 16 to the nozzles of the jet-propelled rotor of the helicopter. In another position of valve 15, the gas is discharged through a duct 17 to exhaust or to a straight jet-propulsion nozzle. The gas is generated in combustion chambers 3 and, after traversing a turbine 4, passes to the valve 15 between cylindrical walls 18, 19, Figs 3 and 4, and is guided into a rectangular duct 20 by means of two guide vanes 27, one on either side, which extend from a single vane 28. In addition, there is a guide vane 29 having curved extensions 30, 31 which extend in a generally horizontal plane towards the discharge end of the turbine 4, and a vertical portion 32 which extends across the duct 20. A vertical partition 35 divides at its lower end into two curved or straight walls which are united to the wall 18. A compressor 5 draws in air through an intake 6 and discharges it into the space between the wall 19 and an outer cylindrical wall 21, where it is guided upwardly by two guide vanes 24, one on either side of the wall 19, into the space between the duct 20 and a further rectangular duct 22. Thus the hot gas from the turbine is jacketed by a stream of cool air which prevents overheating of the valve 15. This jacketing may be retained downstream of the valve. The compressor 5 and a compressor 1 which supplies air to the combustion chambers 3 are both directly driven by the turbine 4.
GB13300/53A 1953-05-12 1953-05-12 Gas producers of the gas turbine type Expired GB764064A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB13300/53A GB764064A (en) 1953-05-12 1953-05-12 Gas producers of the gas turbine type

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB13300/53A GB764064A (en) 1953-05-12 1953-05-12 Gas producers of the gas turbine type

Publications (1)

Publication Number Publication Date
GB764064A true GB764064A (en) 1956-12-19

Family

ID=10020451

Family Applications (1)

Application Number Title Priority Date Filing Date
GB13300/53A Expired GB764064A (en) 1953-05-12 1953-05-12 Gas producers of the gas turbine type

Country Status (1)

Country Link
GB (1) GB764064A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992005343A1 (en) * 1990-09-24 1992-04-02 Siemens Aktiengesellschaft Exhaust system for thermal electric stations, in particular gas turbine stations
WO2014165161A1 (en) * 2013-03-13 2014-10-09 Roach John M Iii Gas turbine engine exhaust fluid passage duct

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992005343A1 (en) * 1990-09-24 1992-04-02 Siemens Aktiengesellschaft Exhaust system for thermal electric stations, in particular gas turbine stations
WO2014165161A1 (en) * 2013-03-13 2014-10-09 Roach John M Iii Gas turbine engine exhaust fluid passage duct
US9909459B2 (en) 2013-03-13 2018-03-06 Rolls-Royce Corporation Gas turbine engine exhaust fluid passage duct

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