GB1085227A - Improvements in or relating to gas turbine engines - Google Patents

Improvements in or relating to gas turbine engines

Info

Publication number
GB1085227A
GB1085227A GB29856/63A GB2985663A GB1085227A GB 1085227 A GB1085227 A GB 1085227A GB 29856/63 A GB29856/63 A GB 29856/63A GB 2985663 A GB2985663 A GB 2985663A GB 1085227 A GB1085227 A GB 1085227A
Authority
GB
United Kingdom
Prior art keywords
boundary layer
gas turbine
gas
hollow
suction
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
GB29856/63A
Inventor
David Morris Brown
Robert Bridge
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB29856/63A priority Critical patent/GB1085227A/en
Publication of GB1085227A publication Critical patent/GB1085227A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D29/324—Blades
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,085,227. Axial flow compressors; gas turbine engines. ROLLS-ROYCE Ltd. July 20, 1964 [July 26, 1963], No. 29856/63. Headings F1C, F1G and F1T. [Also in Division F2] To reduce noise in a gas turbine engine each compressor or turbine rotor blade (preferably of the inlet stages of the compressor or the outlet stages of the turbine) comprises a solid upstream part and a hollow downstream part, said hollow part having a porous or foraminous surface which is exposed to gaseous flow, and suction means connected to the hollow parts of the blades whereby boundary layer gases from the gaseous flow are drawn through the surface to inhibit turbulence in the boundary layer gases. A blade having a solid leading edge 32 is formed with perforations that communicate with a cavity 34 through which boundary layer gas is withdrawn by a suction pump 39. Other embodiments are described embodying single or multiple suction slots or areas of porous material. Similar construction may be used for stator blades. The casing or inner wall of the machine may be perforated. Also, as at 25, and formed with an annular duct 26 through which turbulent boundary layer gas 28 is extracted by a suction device or conduit 27.
GB29856/63A 1963-07-26 1963-07-26 Improvements in or relating to gas turbine engines Expired GB1085227A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB29856/63A GB1085227A (en) 1963-07-26 1963-07-26 Improvements in or relating to gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB29856/63A GB1085227A (en) 1963-07-26 1963-07-26 Improvements in or relating to gas turbine engines

Publications (1)

Publication Number Publication Date
GB1085227A true GB1085227A (en) 1967-09-27

Family

ID=10298322

Family Applications (1)

Application Number Title Priority Date Filing Date
GB29856/63A Expired GB1085227A (en) 1963-07-26 1963-07-26 Improvements in or relating to gas turbine engines

Country Status (1)

Country Link
GB (1) GB1085227A (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3694102A (en) * 1969-07-26 1972-09-26 Daimler Benz Ag Guide blades of axial compressors
US3953325A (en) * 1972-09-27 1976-04-27 Nelson Douglas G Pulp screen with rotating cleaning foil
US4054398A (en) * 1974-08-08 1977-10-18 Caterpillar Tractor Co. Centrifugal compressor or centripetal turbine
WO2001055559A1 (en) * 2000-01-27 2001-08-02 Siemens Aktiengesellschaft Porous turbine blades and turbine equipped with blades of this type
GB2407142A (en) * 2003-10-15 2005-04-20 Rolls Royce Plc An arrangement for bleeding the boundary layer from an aircraft engine
FR2875866A1 (en) * 2004-09-30 2006-03-31 Snecma Moteurs Sa Air circulation method for turbine engine compressor of aircraft, involves sucking air in cavities, driving sucked air inside fixed vanes of each compression stage of compressor, bleeding air inside vanes, and driving air out of compressor
EP1756409A1 (en) * 2004-05-07 2007-02-28 Pratt & Whitney Canada Corp. Shockwave-induced boundary layer bleed for transonic gas turbine
FR2900692A1 (en) * 2006-05-05 2007-11-09 Snecma Sa High pressure compressor blade for turbo-machine of aviation, has suction device with orifices distributed in groups and inclined towards leading edge, and suction channels each communicating with respective group of orifices
EP1536146A3 (en) * 2003-11-26 2008-04-02 Rolls-Royce Deutschland Ltd & Co KG Turbo machine and fluid extraction
WO2011157398A3 (en) * 2010-06-14 2013-04-04 Rolls-Royce Deuschland Ltd. & Co. Kg Noise-reduced turbomachine
CN103321960A (en) * 2013-07-12 2013-09-25 西北工业大学 Compressor stator blade with suction surface provided with suction grooves
RU2515575C2 (en) * 2008-10-17 2014-05-10 Турбомека Gas turbine engine diffuser and gas turbine engine with such diffuser
CN111692116A (en) * 2020-05-22 2020-09-22 哈尔滨工业大学 Suction method and device based on porous medium material
EP3964693A1 (en) * 2020-08-14 2022-03-09 Raytheon Technologies Corporation Active flow control transpirational flow acoustically lined guide vane
US11512608B2 (en) 2020-08-14 2022-11-29 Raytheon Technologies Corporation Passive transpirational flow acoustically lined guide vane

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3694102A (en) * 1969-07-26 1972-09-26 Daimler Benz Ag Guide blades of axial compressors
US3953325A (en) * 1972-09-27 1976-04-27 Nelson Douglas G Pulp screen with rotating cleaning foil
US4054398A (en) * 1974-08-08 1977-10-18 Caterpillar Tractor Co. Centrifugal compressor or centripetal turbine
WO2001055559A1 (en) * 2000-01-27 2001-08-02 Siemens Aktiengesellschaft Porous turbine blades and turbine equipped with blades of this type
GB2407142A (en) * 2003-10-15 2005-04-20 Rolls Royce Plc An arrangement for bleeding the boundary layer from an aircraft engine
GB2407142B (en) * 2003-10-15 2006-03-01 Rolls Royce Plc An arrangement for bleeding the boundary layer from an aircraft engine
US7200999B2 (en) 2003-10-15 2007-04-10 Rolls-Royce Plc Arrangement for bleeding the boundary layer from an aircraft engine
EP1536146A3 (en) * 2003-11-26 2008-04-02 Rolls-Royce Deutschland Ltd & Co KG Turbo machine and fluid extraction
EP1756409A4 (en) * 2004-05-07 2010-04-07 Pratt & Whitney Canada Shockwave-induced boundary layer bleed for transonic gas turbine
EP1756409A1 (en) * 2004-05-07 2007-02-28 Pratt & Whitney Canada Corp. Shockwave-induced boundary layer bleed for transonic gas turbine
US7581920B2 (en) 2004-09-30 2009-09-01 Snecma Method for air circulation in a turbomachine compressor, compressor arrangement using this method, compression stage and compressor incorporating such a arrangement, and aircraft engine equipped with such a compressor
EP1643136A1 (en) * 2004-09-30 2006-04-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Method for circulating air in a turbocompressor
FR2875866A1 (en) * 2004-09-30 2006-03-31 Snecma Moteurs Sa Air circulation method for turbine engine compressor of aircraft, involves sucking air in cavities, driving sucked air inside fixed vanes of each compression stage of compressor, bleeding air inside vanes, and driving air out of compressor
FR2900692A1 (en) * 2006-05-05 2007-11-09 Snecma Sa High pressure compressor blade for turbo-machine of aviation, has suction device with orifices distributed in groups and inclined towards leading edge, and suction channels each communicating with respective group of orifices
RU2515575C2 (en) * 2008-10-17 2014-05-10 Турбомека Gas turbine engine diffuser and gas turbine engine with such diffuser
WO2011157398A3 (en) * 2010-06-14 2013-04-04 Rolls-Royce Deuschland Ltd. & Co. Kg Noise-reduced turbomachine
US9574452B2 (en) 2010-06-14 2017-02-21 Rolls-Royce Deutschland Ltd & Co Kg Noise-reduced turbomachine
CN103321960B (en) * 2013-07-12 2015-07-15 西北工业大学 Compressor stator blade with suction surface provided with suction grooves
CN103321960A (en) * 2013-07-12 2013-09-25 西北工业大学 Compressor stator blade with suction surface provided with suction grooves
CN111692116A (en) * 2020-05-22 2020-09-22 哈尔滨工业大学 Suction method and device based on porous medium material
CN111692116B (en) * 2020-05-22 2022-03-22 哈尔滨工业大学 Suction method and device based on porous medium material
EP3964693A1 (en) * 2020-08-14 2022-03-09 Raytheon Technologies Corporation Active flow control transpirational flow acoustically lined guide vane
US11408349B2 (en) 2020-08-14 2022-08-09 Raytheon Technologies Corporation Active flow control transpirational flow acoustically lined guide vane
US11512608B2 (en) 2020-08-14 2022-11-29 Raytheon Technologies Corporation Passive transpirational flow acoustically lined guide vane

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