GB536238A - Improvements in and relating to internal combustion turbine plants - Google Patents

Improvements in and relating to internal combustion turbine plants

Info

Publication number
GB536238A
GB536238A GB29487/39A GB2948739A GB536238A GB 536238 A GB536238 A GB 536238A GB 29487/39 A GB29487/39 A GB 29487/39A GB 2948739 A GB2948739 A GB 2948739A GB 536238 A GB536238 A GB 536238A
Authority
GB
United Kingdom
Prior art keywords
blades
turbine
ring
air
useful
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
GB29487/39A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB29487/39A priority Critical patent/GB536238A/en
Publication of GB536238A publication Critical patent/GB536238A/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • 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
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • F02C3/085—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage the turbine being of the radial-flow type (radial-radial)
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/105—Centrifugal pumps for compressing or evacuating with double suction
    • 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)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

536,238. Gas turbines. HEPPNER, F. A. M. Nov. 6, 1939, Nos. 29487/39 and 122/40. [Classes 110 (i) and 110 (iii)] The gas turbine 4, Fig. 1, and air-compressor 3 are on one shaft. The useful-power shaft 2 carries a ring of outward flow turbine blades 8 though which the air-compressor discharge passes and this provides the only power connection between the turbine and useful-power shafts. Fuel is admitted at 16 and is burnt in a divergent chamber 11. The turbine comprises a ring of inward flow guide blades 10 and a double axial flow stage 9. Air, flowing between the combustion chamber 11 and the walls 13, passes through the hollow centres of the guide blades 10 before mixing with the gases from the combustion chamber. The combustion chamber wall is divided by three longitudinal slots and the three wall portions are given a slight and overlapping scroll form. Fluid pumps 28, 31 form speedresponsive devices on the turbine and usefulpower shafts and deliver pressure fluids to cylinders 30, 34 which control the fuel valve. A hand control 37 is put in the connecting mechanism. The fluid of the pump 28 is lubricating oil and that of the pump 31 may be the liquid fuel. In the construction shown in Fig. 3, the turbine and pump rotors have fluid channels 22, in lieu of blades, which lead alternately from opposite sides of the rotor and the turbines'have rings of axial-flow blades 23. Passages 26, 24 for cooling air are provided in the turbine rotors and they have outlets 240 in the rotor peripheries. The blades 8 for the useful-power shaft 2 are secured by peening in a disc 19a and in a ring detachably secured in a groove in a disc 19. The latter ring is carried by radial pins on a spider 18. Separate combustion chambers 11 are provided for the two turbines.' In the double axial flow turbine 4, Fig. 1, the blades have ribbed roots and are slidden into helical grooves of steep pitch : there are as many such grooves as blades in a ring. The blades of the first ring have double roots and engage in adjacent grooves. The number of first ring blades is, consequently, half that of succeeding rings.
GB29487/39A 1939-11-06 1939-11-06 Improvements in and relating to internal combustion turbine plants Expired GB536238A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB29487/39A GB536238A (en) 1939-11-06 1939-11-06 Improvements in and relating to internal combustion turbine plants

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB29487/39A GB536238A (en) 1939-11-06 1939-11-06 Improvements in and relating to internal combustion turbine plants

Publications (1)

Publication Number Publication Date
GB536238A true GB536238A (en) 1941-05-07

Family

ID=10292319

Family Applications (1)

Application Number Title Priority Date Filing Date
GB29487/39A Expired GB536238A (en) 1939-11-06 1939-11-06 Improvements in and relating to internal combustion turbine plants

Country Status (1)

Country Link
GB (1) GB536238A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2442169A (en) * 1944-02-17 1948-05-25 Elmer J Hart Power transmission
US2463294A (en) * 1944-04-26 1949-03-01 Edgar W Millard Gasoline turbine engine
US2544418A (en) * 1947-03-22 1951-03-06 Daniel And Florence Guggenheim Driving means for rotating combustion chambers
EP0153066A1 (en) * 1984-02-06 1985-08-28 A/S Kongsberg Väpenfabrikk Dual-entry centrifugal compressor
US4826395A (en) * 1988-04-08 1989-05-02 Westinghouse Electric Corp. Turbine inlet flow deflector and sealing system
EP0801209A2 (en) * 1996-04-12 1997-10-15 ROLLS-ROYCE plc Tip sealing for turbine rotor blade
US5927940A (en) * 1996-08-23 1999-07-27 Pfeiffer Vacuum Gmbh Double-flow gas friction pump

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2442169A (en) * 1944-02-17 1948-05-25 Elmer J Hart Power transmission
US2463294A (en) * 1944-04-26 1949-03-01 Edgar W Millard Gasoline turbine engine
US2544418A (en) * 1947-03-22 1951-03-06 Daniel And Florence Guggenheim Driving means for rotating combustion chambers
EP0153066A1 (en) * 1984-02-06 1985-08-28 A/S Kongsberg Väpenfabrikk Dual-entry centrifugal compressor
US4826395A (en) * 1988-04-08 1989-05-02 Westinghouse Electric Corp. Turbine inlet flow deflector and sealing system
EP0801209A2 (en) * 1996-04-12 1997-10-15 ROLLS-ROYCE plc Tip sealing for turbine rotor blade
EP0801209A3 (en) * 1996-04-12 1999-07-07 ROLLS-ROYCE plc Tip sealing for turbine rotor blade
US6142739A (en) * 1996-04-12 2000-11-07 Rolls-Royce Plc Turbine rotor blades
US5927940A (en) * 1996-08-23 1999-07-27 Pfeiffer Vacuum Gmbh Double-flow gas friction pump

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