GB829727A - High pressure ratio cooling system - Google Patents

High pressure ratio cooling system

Info

Publication number
GB829727A
GB829727A GB36236/57A GB3623657A GB829727A GB 829727 A GB829727 A GB 829727A GB 36236/57 A GB36236/57 A GB 36236/57A GB 3623657 A GB3623657 A GB 3623657A GB 829727 A GB829727 A GB 829727A
Authority
GB
United Kingdom
Prior art keywords
tube
turbine
air
duct
pipe
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
GB36236/57A
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.)
Garrett Corp
Original Assignee
Garrett 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 Garrett Corp filed Critical Garrett Corp
Publication of GB829727A publication Critical patent/GB829727A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
    • F25B9/00—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point
    • F25B9/02—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point using Joule-Thompson effect; using vortex effect
    • F25B9/04—Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point using Joule-Thompson effect; using vortex effect using vortex effect
    • 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

Abstract

829,727. Refrigerating GARRETT CORPORATION. Nov. 20, 1957 [Nov. 21, 1956], No. 36236/57. Class 29 Air to be supplied to an aircraft cabin 36 from a source of compressed air, e.g. the compressor 10 of a gas turbine assembly, is first cooled by a vortex tube 20 and then by an expansion turbine 32. As shown compressed air flows through pipe 16 and valve 50 to the tube and the cold air flows from the tube through pipe 25 and heat exchanger 18 to the turbine 32. The hot end of the tube extends into a duct 44 in which exchanger 18 is located and ambient air is circulated through the duct by fan 40 driven by turbine 32. The hot end of the tube may be closed or partially opened. Exchanger 18 may be omitted and the tube may be wholly or partially by-passed through a valve 48 and pipe 46. Valves 48, 50 may be actuated automatically. Fan 40 may be driven by a jet pump actuated by air bled from the hot end of tube 20. Alternatively ram air may flow through duct 44. Turbine 32 may be constructed as described in Specifications 628,279 or 628,313 or may be replaced by the compressorturbine unit described in Specification 632,678. Specification 405,781 also is referred to.
GB36236/57A 1956-11-21 1957-11-20 High pressure ratio cooling system Expired GB829727A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US829727XA 1956-11-21 1956-11-21

Publications (1)

Publication Number Publication Date
GB829727A true GB829727A (en) 1960-03-09

Family

ID=22174612

Family Applications (1)

Application Number Title Priority Date Filing Date
GB36236/57A Expired GB829727A (en) 1956-11-21 1957-11-20 High pressure ratio cooling system

Country Status (1)

Country Link
GB (1) GB829727A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1987004776A1 (en) * 1986-02-04 1987-08-13 Walter Sibbertsen Process for cooling the blades of thermal turbomachines

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1987004776A1 (en) * 1986-02-04 1987-08-13 Walter Sibbertsen Process for cooling the blades of thermal turbomachines
EP0232782A1 (en) * 1986-02-04 1987-08-19 MAR-RESEARCH Gesellschaft für Forschung und Entwicklung mbH Cooling method and apparatus for thermal turbine vanes
US4818178A (en) * 1986-02-04 1989-04-04 Marresearch Gesellschaft Fuer Forschung Und Entwicklung Gmbh Process for cooling the blades of thermal turbomachines

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