US3883263A - Device for cooling rotor blades with solid profile of motor vehicle gas turbines - Google Patents

Device for cooling rotor blades with solid profile of motor vehicle gas turbines Download PDF

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Publication number
US3883263A
US3883263A US426911A US42691173A US3883263A US 3883263 A US3883263 A US 3883263A US 426911 A US426911 A US 426911A US 42691173 A US42691173 A US 42691173A US 3883263 A US3883263 A US 3883263A
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US
United States
Prior art keywords
rotor
rotor blades
cooling air
blades
peripheral
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 - Lifetime
Application number
US426911A
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English (en)
Inventor
Horst Mai
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.)
AUSBURG NUREMBERG AG
MASCHINENFABRIK AUSBURG-NUREMBERG AG WERK NUREMBERG
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AUSBURG NUREMBERG AG
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 AUSBURG NUREMBERG AG filed Critical AUSBURG NUREMBERG AG
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Publication of US3883263A publication Critical patent/US3883263A/en
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Expired - Lifetime legal-status Critical Current

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    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades

Definitions

  • Appl' A device for cooling the twisted rotor blades with solid profile of a motor vehicle gas turbines according 30 Foreign u gi priority m to which on or in the support for the guiding device Dec 2] 1972 Germany N 2262597 preceding the rotor part, nozzles actuated by cooling air are so arranged that that part of the turbine rotor 52 us.
  • 415mm 415/117 which is adimm the active blade Pwfile is 5
  • the present invention relates to a device for cooling twisted rotor blades with solid profile of motor vehicle gas turbines, according to which on, or in the support for the guiding device preceding the rotor part, nozzles actuated by cool air are so arranged that that part of the turbine rotor which is adjacent to the active blade profile is swept over by cooling air.
  • FIG. 1 is a longitudinal section through a rotor of a vehicle gas turbine and through a portion of the guiding device.
  • FIG. 2 illustrates a section taken along the line "-11 of FIG. 1 and shows a development of the rotor and guide wheel.
  • the device according to the present invention for cooling the rotor blades with solid profile of motor vehicle gas turbines is characterized primarily in that also the guiding device has that portion thereof which overlaps the rotor blade ends provided with a nozzle device adapted to be actuated by cooling air while the nozzles are so arranged that the cooling air flows out in radial direction.
  • cooling device in addition to the drop in temperature from the blade center to the blade base there also exists a drop in temperature from the blade center to the blade head so that the medium rotor blade temperature (equal turbine entrance temperature assumed), is lower than the medium rotor blade temperature of heretofore known turbine rotors with exclusive blade base cooling, so that in conformity with the present invention the life span of the rotor blades is considerably increased.
  • a further advantage of the cooling device according to the invention consists in that the cooling air reduces the loss in working gas through the gap provided between the rotor blade end! and that portion of the guiding device overlapping the latter.
  • nozzles In order to avoid siren-like noises in the rotor part due to the provided nozzles in that part of the guiding device which overlaps the blade ends, it is suggested according to a further feature of the invention to design the nozzles as one or more annular slots.
  • the arrangement shown therein comprises a rotor l of a motor vehicle gas turbine of the axial type, said rotor having a hub 2, a wheel body 3, and the rotor blades 4.
  • the blades 4 are twisted in the heretofore customary manner and while being thin-walled have a solid profile.
  • the rotor l is provided by a guiding device 5 with guiding blades 6.
  • the outer guiding blade ring 7 continues in the direction toward the rotor 1 while being correspondingly reinforced and overlaps the rotor.
  • the extension 8 which is coaxial with the rotor 1 has that part thereof which overlaps the rotor provided with annular slots 9 directed perpendicularly with regard to the rotor axis.
  • the slots 9 communicate through a conduit 10 with a nonillustrated source of compressed cooling air.
  • cooling air may be employed a portion of the air compressed by the compressor of the gas turbine. Expediently, however, if as cooling air there is employed the compressed air which is considerably cooler than the compressor air and is fed directly by the compressed air storage container to the slots 9.
  • an additional cooling device is arranged in the part 12 of the guiding device 5.
  • This last mentioned cooling device serves for cooling the blade base.
  • the cooling device comprises a plurality of nozzles 13 which, through an annular chamber 14, are in communication with a source of compressed air (not illustrated).
  • the cooling air for the rotor blade ends flows under pressure from the slots 9 radially inwardly toward the ends of the rotor.
  • the curvature of the rotor blades 4 brings about on one hand a conveying of the cooling air in a direction counter to the direction of flow of the working gas and on the other hand the flow of working gas brings about a conveying of the air in the direction of the working gas.
  • the cooling air is specifically heavier than the working gas, due to the centrifugal force, a cold air ring remains around the blade ends.
  • a temperature drop toward the blade ends is created. Since, in view of the cooling of the blade base there exists also a temperature drop toward the base of the blades, heat is conveyed radially inwardly and also radially outwardly.
  • a guide wheel coaxially arranged with said rotor and including: a central section extending around said hub, a peripheral section extending around said rotor blades, and guide blades interconnecting said central section and said peripheral section, annular chamber means radially inwardly of said guide wheel blades and provided with first nozzle means di- 3 4 rected and open toward that portion of said turbine blades, said second nozzle means being adapted to be whlch and radlany y of 5314 P connected to a source of compressed cooling air.
  • annular chamber means being adapted to be connected to a source of cooling air, and second nozzle means provided in said peripheral section and directed at least approximately radially least one annular slottoward the peripheral portion of said peripheral rotor 2.
  • second nozzle means includes at

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US426911A 1972-12-21 1973-12-20 Device for cooling rotor blades with solid profile of motor vehicle gas turbines Expired - Lifetime US3883263A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2262597A DE2262597A1 (de) 1972-12-21 1972-12-21 Vorrichtung zum kuehlen von vollprofillaufschaufeln von kraftfahrzeuggasturbinen

Publications (1)

Publication Number Publication Date
US3883263A true US3883263A (en) 1975-05-13

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ID=5865048

Family Applications (1)

Application Number Title Priority Date Filing Date
US426911A Expired - Lifetime US3883263A (en) 1972-12-21 1973-12-20 Device for cooling rotor blades with solid profile of motor vehicle gas turbines

Country Status (4)

Country Link
US (1) US3883263A (it)
DE (1) DE2262597A1 (it)
GB (1) GB1450133A (it)
IT (1) IT1005524B (it)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4732531A (en) * 1986-08-11 1988-03-22 National Aerospace Laboratory of Science and Technoloyg Agency Air sealed turbine blades
US4923370A (en) * 1988-11-28 1990-05-08 Allied-Signal Inc. Radial turbine wheel
WO2000053897A1 (en) * 1999-03-11 2000-09-14 Alm Development, Inc. Gas turbine engine
US6321528B1 (en) 1999-02-23 2001-11-27 Otkrytoe Aktsionernoe Obschestvo “Nauchno-Proizvodstvennoe Obiedinenie “Energomash” Imeni Akademika V.P. Glushko” Turbine, for a liquid-propellant rocket engine mainly
US6363708B1 (en) 1999-10-12 2002-04-02 Alm Development, Inc. Gas turbine engine
US6397576B1 (en) 1999-10-12 2002-06-04 Alm Development, Inc. Gas turbine engine with exhaust compressor having outlet tap control
US6442945B1 (en) 2000-08-04 2002-09-03 Alm Development, Inc. Gas turbine engine
US6460324B1 (en) 1999-10-12 2002-10-08 Alm Development, Inc. Gas turbine engine
GB2413598A (en) * 2004-05-01 2005-11-02 Rolls Royce Plc Providing cooling gas to turbine blade and disc in gas turbine engine
US20110061392A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Combustion cavity layouts for fuel staging in trapped vortex combustors
US20130170954A1 (en) * 2011-12-06 2013-07-04 Alstom Technology Ltd. High Pressure Compressor

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3583824A (en) * 1969-10-02 1971-06-08 Gen Electric Temperature controlled shroud and shroud support
US3791758A (en) * 1971-05-06 1974-02-12 Secr Defence Cooling of turbine blades

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3583824A (en) * 1969-10-02 1971-06-08 Gen Electric Temperature controlled shroud and shroud support
US3791758A (en) * 1971-05-06 1974-02-12 Secr Defence Cooling of turbine blades

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4732531A (en) * 1986-08-11 1988-03-22 National Aerospace Laboratory of Science and Technoloyg Agency Air sealed turbine blades
US4923370A (en) * 1988-11-28 1990-05-08 Allied-Signal Inc. Radial turbine wheel
US6321528B1 (en) 1999-02-23 2001-11-27 Otkrytoe Aktsionernoe Obschestvo “Nauchno-Proizvodstvennoe Obiedinenie “Energomash” Imeni Akademika V.P. Glushko” Turbine, for a liquid-propellant rocket engine mainly
WO2000053897A1 (en) * 1999-03-11 2000-09-14 Alm Development, Inc. Gas turbine engine
US6363708B1 (en) 1999-10-12 2002-04-02 Alm Development, Inc. Gas turbine engine
US6397576B1 (en) 1999-10-12 2002-06-04 Alm Development, Inc. Gas turbine engine with exhaust compressor having outlet tap control
US6460324B1 (en) 1999-10-12 2002-10-08 Alm Development, Inc. Gas turbine engine
US6442945B1 (en) 2000-08-04 2002-09-03 Alm Development, Inc. Gas turbine engine
GB2413598A (en) * 2004-05-01 2005-11-02 Rolls Royce Plc Providing cooling gas to turbine blade and disc in gas turbine engine
US20110061392A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Combustion cavity layouts for fuel staging in trapped vortex combustors
US20110061390A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Inlet premixer for combustion apparatus
US20110061391A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Vortex premixer for combustion apparatus
US20110061395A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Method of fuel staging in combustion apparatus
US8549862B2 (en) 2009-09-13 2013-10-08 Lean Flame, Inc. Method of fuel staging in combustion apparatus
US8689561B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Vortex premixer for combustion apparatus
US8689562B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Combustion cavity layouts for fuel staging in trapped vortex combustors
US20130170954A1 (en) * 2011-12-06 2013-07-04 Alstom Technology Ltd. High Pressure Compressor
US9255479B2 (en) * 2011-12-06 2016-02-09 Alstom Technology Ltd High pressure compressor

Also Published As

Publication number Publication date
IT1005524B (it) 1976-09-30
GB1450133A (en) 1976-09-22
DE2262597A1 (de) 1974-07-11

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