US3389889A - Axial flow rotor - Google Patents

Axial flow rotor Download PDF

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Publication number
US3389889A
US3389889A US643451A US64345167A US3389889A US 3389889 A US3389889 A US 3389889A US 643451 A US643451 A US 643451A US 64345167 A US64345167 A US 64345167A US 3389889 A US3389889 A US 3389889A
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US
United States
Prior art keywords
sleeve
stub
rotor
radially
stubs
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
US643451A
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English (en)
Inventor
Penny Robert Noel
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.)
Rover Co Ltd
Original Assignee
Rover Co 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
Application filed by Rover Co Ltd filed Critical Rover Co Ltd
Application granted granted Critical
Publication of US3389889A publication Critical patent/US3389889A/en
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Expired - Lifetime legal-status Critical Current

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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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • each blade is an openended tubular sleeve carried on a stub extending radially from the rotor body, each stub protruding radially beyond the radially-outer end of the sleeve carried thereby and having a retaining cap secured to its radially-outer end, the retaining cap extending outwardly from the peripheral surface of the stub to form a stop to restrain the sleeve from centrifugal movement on its stub, and in which a blade platform extends circumferentially outwardly from the radially-inner end of each sleeve, the platforms of adjacent sleeves co-operating to shroud the periphery of the body portion between each stub from the working fiuid.
  • the invention relates to a bladed rotor of the axial flow type and is particularly concerned with a rotor having blades capable of withstanding a high operating temperature, e.g., of the order of 1100 C.
  • An object of the invention is to provide a rotor having high tensile strength and also having blades of a ceramic or non-metallic material capable of withstanding a high operating temperature.
  • a bladed rotor of the axial flow type comprises a body portion having a plurality of radially-outwardly extending, blade-supporting stubs spaced apart around its periphery, a plurality of blades each in the form of an open-ended tubular sleeve carried on one of said stubs, each stug protruding radially beyond the radially-outer end of the sleeve carried thereby and having a retaining gap secured to its radially-outer end, the retaining cap extending outwardly from the peripheral surface of the stub to form a stop to be engaged by the radially-outer end of the sleeve, thereby to retain the latter on the stub against centrifugal movement during rotation of the rotor, and a blade platform extending circumferentially outwardly from the radially-inner end of each sleeve, the platforms of adjacent sleeves co-operating to define the radially-inner wall
  • Each sleeve is conveniently a loose fit on the supporting stub, whereby clearance is provided between adjacent surfaces of the stub and the sleeve, the clearance communicating adjacent the radially-inner end of the sleeve with a source of compressed air for cooling the sleeve and the stub and communicating adjacent the radiallyouter end of the sleeve with the working fluid flow path between the blades.
  • the radially-outer end face of the sleeve or the radially-inner end face of the associated retaining cap, or each said end face, may have grooves therein forming outlet passages permitting the cooling air to flow from the clearance into the working fluid flow path during operation of the rotor, when the sleeve is held by centrifugal force in abutment with the retaining cap.
  • the radially-outer of each sleeve may be formed with outlet holes to permit the flow of cooling air 3,389,889 Patented June 25, 1968 ice from the clearance between the sleeve and its supporting stub.
  • the cooling air is conveniently admitted into the clearances from spaces between the platforms and the periphery of the body portion intermediate the stubs.
  • the stubs may be hollow and have internal cooling air passages communicating with the clearances through holes in the stubs adjacent the radially-inner ends thereof.
  • the retaining caps carried by the stubs may be separate from each other or the retaining caps of two or more circumferentially adjacent stubs may be common to said stubs and be of annular or part-annular form.
  • Each sleeve may have an integral shroud extending circumferentially from the outer end thereof, the shrouds of circumferentially adjacent sleeves co-operating to form an annular shroud defining the radially-outer wall of the working fluid flow path.
  • the sleeves are made of a ceramic or other non-metallic material capable of withstanding a high operating temperature egg. of the order of 1100 C., the body portion, the stubs and the retaining caps being made of metal.
  • the securing of the retaining caps to the stubs, after the sleeves have been fitted thereon, may conveniently be performed by welding or brazing. Where the caps are to be welded to the stubs electron-beam welding may be employed.
  • the body portion including integral stubs, is conveniently a precision casting; but it may be fabricated in any other suitable manner.
  • the stubs may be cast integrally with a ring which is then secured around a circular hub, e.g. by electron-beam welding.
  • FIGURE 1 is an exploded, perspective view of a portion of the rotor according to the first construction
  • FIGURE 2 is a half axial cross-section through the rotor, illustrated in FIGURE 1, when assembled;
  • FIGURE 3 is a perspective view showing the portion of the rotor, illustrated in FIGURE 1, when assembled;
  • FIG. 4 is a perspective view similar to FIGURE 3 showing a portion of the rotor according to the second construction.
  • FIGURE 5 is a perspective view similar to FIGURE 3, except that a portion of a blade has been broken away, showing a portion of the rot-or according to the third construction.
  • the rotor comprises a body portion 1 having integral blade-supporting stubs 2, spaced apart around its periphery.
  • the body portion 1 and the stubs 2 are a precision casting.
  • Each stub carries a blade 3 in the form of an open-ended sleeve of ceramic or other non-metallic material.
  • the sleeve 3 is of blade shape in cross-section and has a central throughway 4 through which the stub 2 protrudes.
  • the sleeve 3 is a loose fit on the stub and so clearance is provided between adjacent surfaces of the stub and the sleeve.
  • the protruding radially-outer end of the stub 2 has an end cap 5 welded or similarly secured thereto, e.g., by electron-beam Welding.
  • the profile of the retaining cap 5 is of substantially the same shape and size as the outer peripheral surface of the sleeve 3 and therefore it extends outwardly all around the profile of the stub 2 and forms a stop against which the sleeve will abut when the rotor is rotating, thus preventing the sleeve 3 from moving off the stub 2 under centrifugal force.
  • the radially-outer end face of the sleeve 3 is formed with grooves 6 which provide communication between the clearance between the sleeve 3 and the stub 2 and the working fluid flow path,
  • each sleeve 3 has an integral platform 7 which abuts the platforms of adjacent sleeves in the assembled rotor and thereby for-ms an annular wall defining the radially-inner boundary of the working fluid flow path and also acting to shroud the periphery 8 of the body portion 1 intermediate the stubs 2 from the working fluid.
  • cooling air is admitted into spaces between the periphery 8 of the body portion 1 and the platforms 7. This air flows outwardly in the direction of arrows X through the clearances between each sleeve 3 and its supporting stub 2 and emerges in the working fluid flow path at the radiallyouter ends of the sleeve through the grooves 6.
  • the periphery 8, the stubs 2 and the sleeves 3 are cooled.
  • the stubs 2 and the periphery 8 are shrouded from the hot Working fluid by the non-metallic sleeve 3 and its platform 7.
  • the retaining cap is coated with a protective material capable of withstanding the high working temperature.
  • the tensile loading is carried by the stubs and not by the non-metallic sleeves 3. Therefore the construction is capable of operating at a high working temperature and has a tensile strength comparable with that of a rotor having metallic blades.
  • the cooling air may be derived from any convenient source. For example, it may be bled from a compressor of an engine including the rotor shown in FIGURES 1 to 3, the cooling air being led (as shown in FIGURE 2) through an annular passage 9 surrounding the rotor shaft, to an annular passage 10, bounded on one side by an end face of the body portion '1 and on the other side by a casing 11, and then to the spaces between the periphery 8 of the body portion 1 and the platforms 7.
  • FIGURE 4 The second construction of rotor illustrated by FIGURE 4 is similar to that of FIGURES 1 to 3 with the exception that, instead of the separate retaining caps 5, two or more circumferentially-adjacent stubs 2 are interconnected, after placing the sleeves 3 on the stubs, by an annular plate or part-annular plates which serve, like the retaining caps 5, to hold the sleeves 3 on the respective stubs 2.
  • the plate or plates 15 also form a shroud defining the radially-outer boundary of the working fluid passages between the blades.
  • the plate or plates 15 may be attached to the radially-outer ends of the stubs 2 by welding; e.g., electron-beam welding.
  • welding e.g., electron-beam welding.
  • FIGURE 5 The third construction of rotor illustrated by FIGURE 5 is similar to that of FIGURES 1 to 3 with the exception that, the sleeves 3 are a tighter fit on the stubs 2 so that no clearance is provided therebetween. Instead, the stubs 2 are hollow or have axially-extending passages 16 therein. The passages 16 communicate at their radially-inner ends with the spaces between the platforms 7 and the periphery 8 of the body portion 1 and at their radially-outer ends with the grooves 6, the cooling air flowing in the direction of arrows X. Like parts in FIGURES 1 to 3 and FIG- URE 5 are shown by the same reference numerals. Instead of separate retaining caps 5, an annular plate 15 4 or part-annular retaining plates may be provided, as in FIGURE 4.
  • a bladed rotor of the axial flow type comprising a body portion, a plurality of radially-outwardly extending, blade-supporting stubs spaced apart around the periphery of the body portion, a plurality of open-ended tubular sleeves of a ceramic material capable of withstanding a high operating temperature and carried one on each of said stubs and each defining a blade, and a blade platform extending circumferentially outwardly from the radiallyinner end of each sleeve, the platforms of adjacent sleeves co-operating to define the radially-inner wall of the Working fluid flow path between the blades and also to shroud the periphery of the body portion between each stub from the working fluid, wherein the improvement comprises each sleeve is a loose fit on the supporting stub, whereby clearance is provided between adjacent surfaces of the stub and the sleeve, the clearance communicating adjacent the radially-inner end of the sleeve with a source of compressed air
  • a rotor as claimed in claim 1 in which at least one of the adjacent end faces of each sleeve and its retaining cap has grooves therein forming outlet passages for the cooling air to flow from the clearance between said sleeve and said stub.
  • a rotor as claimed in claim 1 in which the radiallyouter end of each sleeve is formed with outlet holes for cooling air to flow from the clearance between said sleeve and said stub.
  • each said stub has an internal cooling air passage therein communicating with the clearance between the sleeve carried thereon and said stub through holes in the stub adjacent the radiallyinner end thereof.
  • a rotor as claimed in claim 1 in which a retaining cap carried by at least two circumferentially adjacent stubs is common to said stubs and is in the form of at least part of an annulus.
  • each said sleeve has an integral shroud extending circumferentially from the outer end thereof, the shrouds of circumferentially adjacent sleeves co'operating to form an annular shroud defining the radially-outer wall of the working fluid flow path.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US643451A 1966-06-03 1967-06-05 Axial flow rotor Expired - Lifetime US3389889A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB24822/66A GB1119392A (en) 1966-06-03 1966-06-03 Axial flow rotor for a turbine or the like

Publications (1)

Publication Number Publication Date
US3389889A true US3389889A (en) 1968-06-25

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Family Applications (1)

Application Number Title Priority Date Filing Date
US643451A Expired - Lifetime US3389889A (en) 1966-06-03 1967-06-05 Axial flow rotor

Country Status (4)

Country Link
US (1) US3389889A (fr)
CH (1) CH469186A (fr)
DE (1) DE1601635A1 (fr)
GB (1) GB1119392A (fr)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
US4247254A (en) * 1978-12-22 1981-01-27 General Electric Company Turbomachinery blade with improved tip cap
DE3125469A1 (de) * 1980-09-19 1982-05-06 Rockwell International Corp., 90245 El Segundo, Calif. Turbomaschine
US4411597A (en) * 1981-03-20 1983-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Tip cap for a rotor blade
US4480956A (en) * 1982-02-05 1984-11-06 Mortoren-und Turbinen-Union Turbine rotor blade for a turbomachine especially a gas turbine engine
US4519745A (en) * 1980-09-19 1985-05-28 Rockwell International Corporation Rotor blade and stator vane using ceramic shell
US5403158A (en) * 1993-12-23 1995-04-04 United Technologies Corporation Aerodynamic tip sealing for rotor blades
EP0935052A3 (fr) * 1998-02-04 2000-03-29 Mitsubishi Heavy Industries, Ltd. Aube rotorique pour turbine à gaz
US6471474B1 (en) 2000-10-20 2002-10-29 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US6511294B1 (en) 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6524070B1 (en) 2000-08-21 2003-02-25 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US20050169759A1 (en) * 2004-02-02 2005-08-04 General Electric Company Gas turbine flowpath structure
US20070002687A1 (en) * 2005-06-30 2007-01-04 Spx Corporation Mixing impeller and method with pre-shaped tip elements
US20080232956A1 (en) * 2004-01-20 2008-09-25 Stefan Baldauf Turbine Blade and Gas Turbine Equipped with a Turbine Blade
US20140241883A1 (en) * 2013-02-23 2014-08-28 Rolls-Royce Corporation Gas turbine engine component
US20150093249A1 (en) * 2013-09-30 2015-04-02 MTU Aero Engines AG Blade for a gas turbine
US10371162B2 (en) 2016-10-05 2019-08-06 Pratt & Whitney Canada Corp. Integrally bladed fan rotor

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7967555B2 (en) * 2006-12-14 2011-06-28 United Technologies Corporation Process to cast seal slots in turbine vane shrouds
EP2826956A1 (fr) 2013-07-17 2015-01-21 Siemens Aktiengesellschaft Rotor pour une turbomachine thermique

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479057A (en) * 1945-03-27 1949-08-16 United Aircraft Corp Turbine rotor
FR999820A (fr) * 1946-01-11 1952-02-05 Perfectionnements aux turbines à gaz
US2786646A (en) * 1949-08-10 1957-03-26 Power Jets Res & Dev Ltd Bladed rotors for axial flow turbines and similarly bladed fluid flow machines
US2931623A (en) * 1957-05-02 1960-04-05 Orenda Engines Ltd Gas turbine rotor assembly

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479057A (en) * 1945-03-27 1949-08-16 United Aircraft Corp Turbine rotor
FR999820A (fr) * 1946-01-11 1952-02-05 Perfectionnements aux turbines à gaz
FR57426E (fr) * 1946-01-11 1953-01-28 Perfectionnements aux turbines à gaz
US2786646A (en) * 1949-08-10 1957-03-26 Power Jets Res & Dev Ltd Bladed rotors for axial flow turbines and similarly bladed fluid flow machines
US2931623A (en) * 1957-05-02 1960-04-05 Orenda Engines Ltd Gas turbine rotor assembly

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
US4247254A (en) * 1978-12-22 1981-01-27 General Electric Company Turbomachinery blade with improved tip cap
DE3125469A1 (de) * 1980-09-19 1982-05-06 Rockwell International Corp., 90245 El Segundo, Calif. Turbomaschine
US4519745A (en) * 1980-09-19 1985-05-28 Rockwell International Corporation Rotor blade and stator vane using ceramic shell
US4411597A (en) * 1981-03-20 1983-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Tip cap for a rotor blade
US4480956A (en) * 1982-02-05 1984-11-06 Mortoren-und Turbinen-Union Turbine rotor blade for a turbomachine especially a gas turbine engine
US5403158A (en) * 1993-12-23 1995-04-04 United Technologies Corporation Aerodynamic tip sealing for rotor blades
EP0935052A3 (fr) * 1998-02-04 2000-03-29 Mitsubishi Heavy Industries, Ltd. Aube rotorique pour turbine à gaz
US6152695A (en) * 1998-02-04 2000-11-28 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade
US6511294B1 (en) 1999-09-23 2003-01-28 General Electric Company Reduced-stress compressor blisk flowpath
US6524070B1 (en) 2000-08-21 2003-02-25 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US6471474B1 (en) 2000-10-20 2002-10-29 General Electric Company Method and apparatus for reducing rotor assembly circumferential rim stress
US20100008773A1 (en) * 2004-01-20 2010-01-14 Stefan Baldauf Turbine blade and gas turbine equipped with a turbine blade
US20080232956A1 (en) * 2004-01-20 2008-09-25 Stefan Baldauf Turbine Blade and Gas Turbine Equipped with a Turbine Blade
US7607889B2 (en) * 2004-01-20 2009-10-27 Siemens Aktiengesellschaft Turbine blade and gas turbine equipped with a turbine blade
US7963746B2 (en) 2004-01-20 2011-06-21 Siemens Aktiengesellschaft Turbine blade and gas turbine equipped with a turbine blade
US7094021B2 (en) * 2004-02-02 2006-08-22 General Electric Company Gas turbine flowpath structure
US20050169759A1 (en) * 2004-02-02 2005-08-04 General Electric Company Gas turbine flowpath structure
US20070002687A1 (en) * 2005-06-30 2007-01-04 Spx Corporation Mixing impeller and method with pre-shaped tip elements
US7481573B2 (en) * 2005-06-30 2009-01-27 Spx Corporation Mixing impeller with pre-shaped tip elements
US20140241883A1 (en) * 2013-02-23 2014-08-28 Rolls-Royce Corporation Gas turbine engine component
US9617857B2 (en) * 2013-02-23 2017-04-11 Rolls-Royce Corporation Gas turbine engine component
US20150093249A1 (en) * 2013-09-30 2015-04-02 MTU Aero Engines AG Blade for a gas turbine
US10371162B2 (en) 2016-10-05 2019-08-06 Pratt & Whitney Canada Corp. Integrally bladed fan rotor

Also Published As

Publication number Publication date
DE1601635A1 (de) 1970-06-18
GB1119392A (en) 1968-07-10
CH469186A (fr) 1969-02-28

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