GB831770A - Compressor-turbine unit - Google Patents

Compressor-turbine unit

Info

Publication number
GB831770A
GB831770A GB5384/58A GB538458A GB831770A GB 831770 A GB831770 A GB 831770A GB 5384/58 A GB5384/58 A GB 5384/58A GB 538458 A GB538458 A GB 538458A GB 831770 A GB831770 A GB 831770A
Authority
GB
United Kingdom
Prior art keywords
duct
turbine
compressor
cavity
scavenge
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
GB5384/58A
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 GB831770A publication Critical patent/GB831770A/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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F01D25/125—Cooling of bearings
    • 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
    • F01D25/18—Lubricating arrangements
    • F01D25/183—Sealing 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
    • 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
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • 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)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

831,770. Gas-turbine plant. UNITED AIRCRAFT CORPORATION. Feb. 19, 1958 [June 20, 1957], No. 5384/58. Class 110 (3) [Also in Group XXXIV] In a lubricating and cooling system for the bearings 18, 20 of a high-speed compressor and turbine assembly having a compressor 12 and a turbine 14 mounted at the ends of a shaft 16 rotatably supported by the bearings 18, 20 in a housing 26, an impeller 22, carried by the shaft and having blades 24, circulates a lubricant mist through a cavity 28 which is closed at its ends by plates 30, 32 and in which the bearings 18, 20 are disposed. In order to ensure that no lubricant mist escapes from the cavity 28, compressed scavenge air, bled from the compressor through a seal 60 and a labyrinth type seal 62, is introduced into the cavity 28 through labyrinth type seals 34, 36 on the plates 30, 32 respectively, scavenge air being supplied to the seal 36 through duct 66 in the housing 26 and duct 68 in the plate 32. Lubricant, e.g. oil, drawn by the impeller, with or without the aid of a pump according to the speed of the compressor and turbine unit, from a sump 70 through a duct 74 passes through a jet 78 in an annular chamber 76 opening out into the area of the impeller blades 24. The scavenge air flow joins the mist flow in cavity 28 and passes through a duct 86 to the sump 70 and then through either of two pipes 94, 96 to a separator 72, the lubricant-free air then being fed to a turbine discharge duct through a line 98. A vent 88, with a relief valve 90, connects the scavenge area B with a turbine discharge chamber 92 and determines the pressure difference between the scavenge area B and the cavity 28. Compressed air, e.g. from an aircraft engine is introduced through a duct 42 to the inlet of the compressor 12 which discharges it to a collector manifold 48 leading through a line 49 to a duct 50 connected to the inlet of the turbine 14. The cooler air, issuing from the turbine in a passage 54 leading to the chamber 92 and scrubbing the outer surface 56 of the housing 26 to cool it, passes through a duct for admission, e.g. to an aircraft pressurized cabin.
GB5384/58A 1957-06-20 1958-02-19 Compressor-turbine unit Expired GB831770A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US831770XA 1957-06-20 1957-06-20

Publications (1)

Publication Number Publication Date
GB831770A true GB831770A (en) 1960-03-30

Family

ID=22176670

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5384/58A Expired GB831770A (en) 1957-06-20 1958-02-19 Compressor-turbine unit

Country Status (2)

Country Link
FR (1) FR1203602A (en)
GB (1) GB831770A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2535526A1 (en) * 2011-06-17 2012-12-19 Aktiebolaget SKF Turbocharger, notably for a combustion engine.
CN103573711A (en) * 2012-08-07 2014-02-12 哈米尔顿森德斯特兰德公司 Motor housing

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6014246U (en) * 1983-07-08 1985-01-30 トヨタ自動車株式会社 Turbo gear oil leak prevention device
EP0143182A1 (en) * 1983-09-01 1985-06-05 BBC Brown Boveri AG Two-stage exhaust turbo charger having a device to avoid lubricant losses

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2535526A1 (en) * 2011-06-17 2012-12-19 Aktiebolaget SKF Turbocharger, notably for a combustion engine.
EP2698504A1 (en) * 2011-06-17 2014-02-19 Aktiebolaget SKF Turbocharger, notably for a combustion engine
CN103573711A (en) * 2012-08-07 2014-02-12 哈米尔顿森德斯特兰德公司 Motor housing
CN103573711B (en) * 2012-08-07 2016-05-25 哈米尔顿森德斯特兰德公司 Motor shell

Also Published As

Publication number Publication date
FR1203602A (en) 1960-01-20

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