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GB802906A - Improvements in or relating to combustion turbine engines comprising axial flow compressors - Google Patents

Improvements in or relating to combustion turbine engines comprising axial flow compressors

Info

Publication number
GB802906A
GB802906A GB468/55A GB46855A GB802906A GB 802906 A GB802906 A GB 802906A GB 468/55 A GB468/55 A GB 468/55A GB 46855 A GB46855 A GB 46855A GB 802906 A GB802906 A GB 802906A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
air
passage
rotor
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
GB468/55A
Inventor
Reginald Henry Doug Chamberlin
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
Priority to BE544238D priority Critical patent/BE544238A/xx
Application filed by D Napier and Son Ltd filed Critical D Napier and Son Ltd
Priority to GB468/55A priority patent/GB802906A/en
Priority to DE1956N0011689 priority patent/DE1050123B/en
Priority to CH355326D priority patent/CH355326A/en
Priority to FR1140041D priority patent/FR1140041A/en
Publication of GB802906A publication Critical patent/GB802906A/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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling 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
    • 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
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

802,906. Gas turbine engines; axial-flow compressors. NAPIER & SON, Ltd., D. Dec. 22, 1955 [Jan. 6, 1955], No. 468/55. Classes 110 (1) and 110 (3). In a gas turbine engine of the kind comprising an axial-flow compressor, one or more combustion chambers and a turbine mounted coaxially with and driving the compressor, an air bleed passage leads inwards from the annular working passage of the compressor towards the compressor rotor axis. A duct arranged coaxially with the compressor rotor communicates with the air bleed passage and leads towards the turbine, means also being provided for delivering cooling air from the duct outwards to the turbine rotor. The air bleed passage leading inwards from the compressor working fluid passage is formed by a non-rotary structure connected to the stator of the compressor and provided with curved vanes which convert the rotational movement of the air at least partly into movement with a component towards the axis of rotation of the compressor. In the embodiment described the compressor has twelve stages, the last two stages being shown in Fig. 2 and comprising blade rows 10, 11 mounted on discs 15, 16 which are in splined engagement with the hollow turbine-compressor shaft 4. The interstage guide vanes 12 carry at their inner ends an annular wall member 21 and a second wall member 22 is secured to the member 21 by means of rivets 25. The wall 22 is provided with curved guide vanes 24, Fig. 3, so that a passage is provided between the two walls 21, 22. The rivets 25 pass through the vanes 24. Apertures 26 are also provided in the vanes 24 and walls 21, 22. Air is led from the downstream side of the guide vanes 12 through the passage between the walls 21, 22 to an annular chamber 30 formed by the rotor discs 15, 16 and thence through four radial outlets 31 into four radial conduits 32 in the hollow shaft 4. The air then enters a duct 33 mounted coaxially within the shaft 4 and flows towards the turbine being discharged through radial outlets across the turbine rotor. Some air could also flow to a balance piston and to the bearings for cooling purposes. The periphery of the disc 17 secured to the shaft 4 forms a seal with the inner wall 18 of the diffuser duct 13. Gas seals are also provided between the walls 21, 22 of the non- rotary structure and the portions 28, 29 of the rotor discs 15, 16.
GB468/55A 1955-01-06 1955-01-06 Improvements in or relating to combustion turbine engines comprising axial flow compressors Expired GB802906A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
BE544238D BE544238A (en) 1955-01-06
GB468/55A GB802906A (en) 1955-01-06 1955-01-06 Improvements in or relating to combustion turbine engines comprising axial flow compressors
DE1956N0011689 DE1050123B (en) 1955-01-06 1956-01-04 Internal combustion turbine system with axial pressure compressor
CH355326D CH355326A (en) 1955-01-06 1956-01-05 Gas turbine plant
FR1140041D FR1140041A (en) 1955-01-06 1956-01-06 Improvements to axial type compressors and gas turbine engines including such compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB468/55A GB802906A (en) 1955-01-06 1955-01-06 Improvements in or relating to combustion turbine engines comprising axial flow compressors

Publications (1)

Publication Number Publication Date
GB802906A true GB802906A (en) 1958-10-15

Family

ID=9704890

Family Applications (1)

Application Number Title Priority Date Filing Date
GB468/55A Expired GB802906A (en) 1955-01-06 1955-01-06 Improvements in or relating to combustion turbine engines comprising axial flow compressors

Country Status (5)

Country Link
BE (1) BE544238A (en)
CH (1) CH355326A (en)
DE (1) DE1050123B (en)
FR (1) FR1140041A (en)
GB (1) GB802906A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2235019A (en) * 1989-06-23 1991-02-20 United Technologies Corp Seal vent bypass conduit for gas turbine engine
GB2445083A (en) * 2006-12-20 2008-06-25 Gen Electric Gas turbine engine having air directed through a duct in the spool shaft
CN102200030A (en) * 2010-03-26 2011-09-28 通用电气公司 Turbine rotor wheel
WO2016072998A1 (en) * 2014-11-07 2016-05-12 General Electric Company Compressor bleed passage with auxiliary impeller in an axial shaft bore
CN112360761A (en) * 2021-01-12 2021-02-12 中国航发上海商用航空发动机制造有限责任公司 Centripetal pressurization air entraining device and system
CN113586630A (en) * 2021-08-02 2021-11-02 山东泰鑫汽车科技有限公司 Last back turbine of deciding of reinforcing hydraulic retarber

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2235019A (en) * 1989-06-23 1991-02-20 United Technologies Corp Seal vent bypass conduit for gas turbine engine
GB2445083A (en) * 2006-12-20 2008-06-25 Gen Electric Gas turbine engine having air directed through a duct in the spool shaft
US7934901B2 (en) 2006-12-20 2011-05-03 General Electric Company Air directing assembly and method of assembling the same
GB2445083B (en) * 2006-12-20 2011-10-26 Gen Electric Air directing assembly and method of assembling the same
CN102200030A (en) * 2010-03-26 2011-09-28 通用电气公司 Turbine rotor wheel
CN102200030B (en) * 2010-03-26 2015-05-27 通用电气公司 Turbine rotor wheel
WO2016072998A1 (en) * 2014-11-07 2016-05-12 General Electric Company Compressor bleed passage with auxiliary impeller in an axial shaft bore
CN112360761A (en) * 2021-01-12 2021-02-12 中国航发上海商用航空发动机制造有限责任公司 Centripetal pressurization air entraining device and system
CN113586630A (en) * 2021-08-02 2021-11-02 山东泰鑫汽车科技有限公司 Last back turbine of deciding of reinforcing hydraulic retarber
CN113586630B (en) * 2021-08-02 2023-05-02 山东泰鑫汽车科技有限公司 Rear turbine on enhanced hydraulic retarder

Also Published As

Publication number Publication date
FR1140041A (en) 1957-07-09
BE544238A (en) 1900-01-01
CH355326A (en) 1961-06-30
DE1050123B (en) 1959-02-05

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