US2559131A - Hollow blade for gas turbines and the like - Google Patents

Hollow blade for gas turbines and the like Download PDF

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Publication number
US2559131A
US2559131A US86703A US8670349A US2559131A US 2559131 A US2559131 A US 2559131A US 86703 A US86703 A US 86703A US 8670349 A US8670349 A US 8670349A US 2559131 A US2559131 A US 2559131A
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US
United States
Prior art keywords
blade
root
pin
assembly
cooling fluid
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
US86703A
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English (en)
Inventor
Oestrich Hermann
Rosskopf Hans
Renner Alfred
Valter Jakob
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OESTRICH
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OESTRICH
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Publication date
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Publication of US2559131A publication Critical patent/US2559131A/en
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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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade

Definitions

  • the cooling fluid is introduced either laterally through ports provided in the vicinity of the root of the blade on the leading edge and the trailing edge of the latter or again through a recess provided between the root of the blade and the blade carrier, said recess being provided in one side of theroot assuming the shape of a case, which I side extends beyond the blade carrier.
  • the channels feeding the blades communicate with a chamber formed by a covering metal sheet and the blade carrier and into which is introduced the cooling fluid.
  • the drawbacks of known blades of this type consist in that they hardly satisfy the conditions of mechanical resistance and of secure fixation that are necessary for turbine blades, that the root of the blade and corresponding recess in the blade carrier are of a comparatively dimcult execution, that the securing inside the blade of the diaphragm intended for instance for the guiding of the cooling medium is a difficult matter, that the blades are interchangeable with some difllculty and the introduction of the cooling fluid into the blade leads to considerable losses by reason of the marked bands of the circuit and unavoidable losses.
  • the object of the invention is to provide a hollow blade that allows removing the above drawbacksand also the execution of a blade root, starting from a single blank of sheet metal. This is obtained by forming the blade in the following manner:
  • the metal sheet forming the wall of the blade is bent at one end so as to form the root, the cross-section of which assumes preferably the shape of a segment of a circle.
  • the connection between the root and the body of the blade is performed at the ends of said segment along both sides of the bent blade through a plane 13 Claims. (01. 60-41) surface that provides together with the root for the fitting and guiding of the blade over the turbine wheel.
  • the root is reinforced by an inserted pin and shows at its lower end one or more openings intended for the axial passage of the cooling fluid from the turbine wheel.
  • the hollow blade forming the object of the invention includes therefore a Laval type or similar root, that is well known per se and has proved satisfactory for solid blades.
  • Fig. 1 is a lateral elevational view of a hollow blade according to the invention.
  • Fig. 2 is 'a cross-section on a larger scale through line AA of Fig. 1.
  • Fig. 3 is a cross-section through line BB of Fig. 2.
  • Fig. 4 illustrates a modified shape that may be given to the trailing edge of the blade.
  • Figs. 5, 6 and 7 illustrate respectively in elevational view, in cross-sectional view and in longi- 'tudinal section a flat blank of sheet metal used for executing the blade.
  • Figs. 8 and 9 illustrate a manner of mounting the blade according to the invention on a turbine rotor.
  • Fig. 8 is a partial elevational view of the rotor seen from the side corresponding to the leading edge while Fig. 9 is a crosssection through line 12-13 of Fig. 8.
  • the blade shown in Figs. 1 to 3 is obtained through the folding inside dies, by means of shaped tools, of a flat blank of sheet metal as illustrated in Figs. 5, 6 and 7.
  • the pin 4 is welded to the sheet metal forming the blade at both ends of said spindle and along the joining surface 6.
  • the welding seam 8 provided on the side corresponding to the leading edge of the blade extends throughout the periphery of the pin 4 while the welding for the side corresponding to the trailing edge of the blade extends only over the lower half of the root for reasons of mechanical resistance.
  • the welding seam closing the body I of the blade extends over the trailing edge 10 only up to a point ll (Fig. 1) From this standpoint, it should be remarked that it is also possible to weld the pin 4 to the sheet metal forming the blade I and also to weld the latter along the joint 6 and further to weld the trailing edge It] in a manner such that the blade may be hermetically sealed throughout its surface except for the opening 5 provided in the root for the introduction of the cooling fluid and also for the opening provided for the output of said cooling fluid that is preferably provided at the tip of said blade.
  • the pin 4 In register with the opening 5, the pin 4 assumes a lesser cross-section so that the cooling fluid may pass into the inside of the blade to either side of the reduced pin portion 40. along the direction illustrated by the arrows.
  • the crosssection of the reduced part of the pin may be given any desired shape.
  • the pin may be constituted by two separate members that are fitted into the root through the opposed ends thereof.
  • the blade includes as in the embodiment illustrated a diaphragm l2 that serves for guiding the cooling air or for damping the vibrations or again simultaneously for both purposes said diaphragm' 12 engages the slot I3 of the pin 4 and extends into the lower end of the root where it is welded to the pin 4.
  • the root illustrated that has a transversal cross-section in the shape of a circular sector may be replaced by a-root of any desired crosssection that may be for instance square, rectanguerated through points or along a continuous line.
  • the starting material used for producing the blade through a folding of a flat sheet of metal is constituted according to the invention by a blank l5 cut to the desired shape as illustrated in Figs. 5, 6 and '7.
  • said blank appears substantially as a rectangular member provided at one end with four rectangular lugs, l6-l1--l8-l9 adapted to'form the root of the blade.
  • the size and spacing of the lugs are defined by the size of the openings to be provided in the root and by the diameter of the latter. It is preferable to make use of a metal sheet the thickness of which gradually decreases from the root towards the tip of the blade as illustrated in Fig. 7, that is a cross-section through line D-D of Fig. 5.
  • the two edges Illa and lb of the blank that are to bear against one another after folding so as to form the trailing edge ll) of the blade are bevelled on their inner side in the manner illustrated in Fig. 6, that is a cross-section through line C-C of Fig. 5.
  • the depth of the bevel diminishes gradually from the root towards the tip of the blade as shown in dotted lines at 20a. and 20b in Fig. 5.
  • Figs. 8 and 9 In the manner of mounting the blade according to the invention on a turbine wheel as illustrated in Figs. 8 and 9, said blade is fitted in corresponding grooves 2
  • the reference number 23 designates the disc of the wheel carrying the blades while .24 designates a locking ring engaging the grooves [4 of the different blades, 25 a balancing member and 26 one of the channels provided through the rim 22 and through which the cooling fluid is fed to the blade or to the openings 5 provided in the root of the blades and progressing in the direction of the arrows.
  • Fig. 8 shows in interrupted lines three such channels 26 that receive the cooling fluid from the chamber 21 formed by the disc 23, the rim 22 and the cover 28. This cooling fluid is fed to said chamber through suitable ducts that are not illustrated.
  • the cooling fluid is admitted into the blade and flows through same without any sharp turns and the channelling system shows no leaking point.
  • an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body atthe root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to saidhollow body.
  • An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length, corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body 3.
  • an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass
  • the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly, flat portions being provided between said body and the bent part of said lugs, said flat portions being parallel with one another and spaced by a distance less than the maximal width of said tubular assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
  • An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length, corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a cylindrical tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
  • an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly, a welded seam being provided between the abutted ends of said lugs at the lower part of said root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
  • an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; and a pin fitted in said assembly, said assembly having an aperture therethrough and said pin including two parts separated by a gap registering with said aperture to provide a cooling fluid inlet passage to said hollow body.
  • an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly; a pin provided with a diametrical slot fitted in said assembly and a metal sheet diaphragm located longitudinally inside the blade and including an extension engaging said slot in said pin and welded to said pin, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
  • an inwardly cooled blade for gas turbines or the like machines having a hollow sheet metal body through which a cooling fluid is adapted to pass, the provision of corresponding lugs projecting from said body at the root end of the front and rear end thereof, said lugs being bent with their outer ends in abutting relationship so as to form a polygonal tubular root assembly; and a pin fitted in said assembly, said assembly and said pin having corresponding apertures therethrough to provide a cooling fluid inlet passage to said hollow body.
  • An inwardly cooled blade for gas turbines or the like machines comprising in combination a hollow sheet metal body through which a cooling fluid is adapted to pass constituted by a blank folded longitudinally through the major part of its length; two pairs of spaced lugs projecting from said hollow body at the root end of the front and rear part thereof respectively, said lugs being bent with their outer ends in abutting relationship so as to form a tubular root assembly 7 provided with a central aperture therethrouth; UNITED STATES PATENTS and a pin fitted in said assembly, said pin havina Number Name m apertm thelfithrou h corresponding to 33m B65373 Budd Jan 15 1901 central aperture to provide a cooling fluid inlet 752,340 Hohwarth Feb.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Reduction Rolling/Reduction Stand/Operation Of Reduction Machine (AREA)
US86703A 1948-04-22 1949-04-11 Hollow blade for gas turbines and the like Expired - Lifetime US2559131A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR664938X 1948-04-22

Publications (1)

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US2559131A true US2559131A (en) 1951-07-03

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US86703A Expired - Lifetime US2559131A (en) 1948-04-22 1949-04-11 Hollow blade for gas turbines and the like

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US (1) US2559131A (ja)
DE (1) DE855178C (ja)
FR (1) FR965814A (ja)
GB (1) GB664938A (ja)
IT (1) IT454293A (ja)

Cited By (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2642263A (en) * 1951-01-05 1953-06-16 Westinghouse Electric Corp Blade apparatus
US2647368A (en) * 1949-05-09 1953-08-04 Hermann Oestrich Method and apparatus for internally cooling gas turbine blades with air, fuel, and water
US2699584A (en) * 1950-02-28 1955-01-18 Woodworth Ind Process Company Flint tube mold and method of making the same
US2708564A (en) * 1952-02-29 1955-05-17 Westinghouse Electric Corp Turbine apparatus
US2719294A (en) * 1953-02-17 1955-10-04 Wilson Jones Co Staple gun tacker
US2762114A (en) * 1951-08-28 1956-09-11 Gen Motors Corp Method of making sheet metal turbine bucket
US2772851A (en) * 1950-06-14 1956-12-04 Stalker Dev Company Rotor construction
US2783023A (en) * 1950-04-05 1957-02-26 Stalker Dev Company Fluid rotor having damping means
US2801072A (en) * 1949-11-22 1957-07-30 Hermann Oestrich Hollow blade for fluid flow operated machine
US2801073A (en) * 1952-06-30 1957-07-30 United Aircraft Corp Hollow sheet metal blade or vane construction
US2809802A (en) * 1952-09-10 1957-10-15 Gen Electric Damping turbine blades
US2823889A (en) * 1950-04-05 1958-02-18 Stalker Dev Company Rotor construction and fabrication
US2828940A (en) * 1953-12-30 1958-04-01 United Aircraft Corp Cooled turbine blade
US2849209A (en) * 1950-10-11 1958-08-26 Gen Electric Nozzle construction for turbines
US2859011A (en) * 1953-07-27 1958-11-04 Gen Motors Corp Turbine bucket and liner
US2863633A (en) * 1952-04-19 1958-12-09 Stalker Dev Company Hollow blades and manufacture thereof
US2869611A (en) * 1955-03-18 1959-01-20 Stalker Dev Company Apparatus including a female die receiving a reciprocating articulated male die for stretch-forming hollow blades
US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
US2875948A (en) * 1953-01-19 1959-03-03 Stalker Dev Company Thin wall bladed wheels for axial flow machines
US2916808A (en) * 1955-03-28 1959-12-15 Gen Electric Method of making a blade for turbomachines
US2954208A (en) * 1953-01-09 1960-09-27 Gen Motors Corp Air foil section
US2976014A (en) * 1952-01-19 1961-03-21 Bbc Brown Boveri & Cie Blading for use in axial flow machines
US2979809A (en) * 1956-03-14 1961-04-18 Napier & Son Ltd Method of making hollow turbine blades
US3002265A (en) * 1957-02-14 1961-10-03 Stalker Corp Fabrication of blades for compressors and the like
US3010696A (en) * 1955-09-26 1961-11-28 Rolls Royce Bladed rotor with means to supply fluid to passages in the blades
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
US3027138A (en) * 1951-12-10 1962-03-27 Power Jets Res & Dev Ltd Turbine blades
US3039739A (en) * 1958-11-28 1962-06-19 Gen Motors Corp Pinned blade connecting means
US3045967A (en) * 1952-04-12 1962-07-24 Stalker Corp Hollow blades and manufacture thereof
US3083446A (en) * 1950-06-14 1963-04-02 Stalker Corp Rotor construction
US3388888A (en) * 1966-09-14 1968-06-18 Gen Electric Cooled turbine nozzle for high temperature turbine
US3697192A (en) * 1970-05-07 1972-10-10 United Aircraft Corp Hollow turbine blade
US3747182A (en) * 1970-05-07 1973-07-24 United Aircraft Corp Method of fabricating a hollow turbine blade having an insert therein
US4037990A (en) * 1976-06-01 1977-07-26 General Electric Company Composite turbomachinery rotor
US5022824A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pinned airfoil propeller blade
US5022825A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pitch retention member
US5102300A (en) * 1988-10-07 1992-04-07 United Technologies Corporation Pinned airfoil propeller assembly
US5205714A (en) * 1990-07-30 1993-04-27 General Electric Company Aircraft fan blade damping apparatus
US6283707B1 (en) * 1999-03-19 2001-09-04 Rolls-Royce Plc Aerofoil blade damper
JP2013072333A (ja) * 2011-09-27 2013-04-22 Mitsubishi Heavy Ind Ltd 静翼及び蒸気タービン

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE944645C (de) * 1952-08-08 1956-06-21 Max Adolf Mueller Dipl Ing Zellenradlaeufer fuer Zellenradschleusen fuer Gasturbinen und Strahltriebwerke
US2853272A (en) * 1952-09-12 1958-09-23 Napier & Son Ltd Hollow blades for turbo machines
JP4355396B2 (ja) 1999-06-04 2009-10-28 富士フイルムファインケミカルズ株式会社 ジアリールアミンの製造方法
FR3087484B1 (fr) * 2018-10-18 2021-01-15 Safran Aircraft Engines Aube de turbomachine

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US665873A (en) * 1900-06-02 1901-01-15 American Pulley Co Sheet-metal spoke-blank.
US752340A (en) * 1904-04-16 A corpora
US1268775A (en) * 1917-04-11 1918-06-04 Nathan Stanger Bail-guard.
US1530249A (en) * 1922-09-23 1925-03-17 Gen Electric Turbine bucket
US1601402A (en) * 1921-01-15 1926-09-28 Lorenzen Christian Gas turbine
GB359349A (en) * 1930-03-03 1931-10-22 Ltd Co Formerly Skoda Works Method of producing a hollow blade for steam and gas turbines
US2220420A (en) * 1938-02-08 1940-11-05 Bbc Brown Boveri & Cie Means for cooling machine parts
US2251926A (en) * 1939-05-18 1941-08-12 American Can Co Container
US2297446A (en) * 1938-12-03 1942-09-29 Zellbeck Gustav Hollow blade for exhaust gas turbine rotors
US2357628A (en) * 1944-09-05 Blade
US2409966A (en) * 1942-01-14 1946-10-22 Universal Slide Fastener Co In Blank for use in the manufacture of sliders for slide fasteners
US2459428A (en) * 1945-04-19 1949-01-18 Briggs & Stratton Corp Air cleaner
US2482990A (en) * 1948-02-09 1949-09-27 Sealed Power Corp Piston ring blank

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DE522992C (de) * 1928-09-27 1931-04-22 Vladimir Kalabek Mehrstufige Gasturbine, bei der das gasfoermige Kuehlmittel zur Arbeitsleistung herangezogen wird
DE557860C (de) * 1930-01-17 1932-08-29 Lorenzen G M B H C Aus zwei Scheiben bestehender Laeufer fuer Gasturbinen und Kreiselverdichter
DE737479C (de) * 1939-01-26 1943-07-15 Versuchsanstalt Fuer Luftfahrt Gasturbinenschaufel
DE735668C (de) * 1940-04-26 1943-05-21 Maschf Augsburg Nuernberg Ag Gasturbinenrad aus keramischem Werkstoff
DE724470C (de) * 1940-10-20 1942-08-27 Versuchsanstalt Fuer Luftfahrt Innengekuehlte Gasturbinenschaufel

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Publication number Priority date Publication date Assignee Title
US2357628A (en) * 1944-09-05 Blade
US752340A (en) * 1904-04-16 A corpora
US665873A (en) * 1900-06-02 1901-01-15 American Pulley Co Sheet-metal spoke-blank.
US1268775A (en) * 1917-04-11 1918-06-04 Nathan Stanger Bail-guard.
US1601402A (en) * 1921-01-15 1926-09-28 Lorenzen Christian Gas turbine
US1530249A (en) * 1922-09-23 1925-03-17 Gen Electric Turbine bucket
GB359349A (en) * 1930-03-03 1931-10-22 Ltd Co Formerly Skoda Works Method of producing a hollow blade for steam and gas turbines
US2220420A (en) * 1938-02-08 1940-11-05 Bbc Brown Boveri & Cie Means for cooling machine parts
US2297446A (en) * 1938-12-03 1942-09-29 Zellbeck Gustav Hollow blade for exhaust gas turbine rotors
US2251926A (en) * 1939-05-18 1941-08-12 American Can Co Container
US2409966A (en) * 1942-01-14 1946-10-22 Universal Slide Fastener Co In Blank for use in the manufacture of sliders for slide fasteners
US2459428A (en) * 1945-04-19 1949-01-18 Briggs & Stratton Corp Air cleaner
US2482990A (en) * 1948-02-09 1949-09-27 Sealed Power Corp Piston ring blank

Cited By (41)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647368A (en) * 1949-05-09 1953-08-04 Hermann Oestrich Method and apparatus for internally cooling gas turbine blades with air, fuel, and water
US2801072A (en) * 1949-11-22 1957-07-30 Hermann Oestrich Hollow blade for fluid flow operated machine
US2699584A (en) * 1950-02-28 1955-01-18 Woodworth Ind Process Company Flint tube mold and method of making the same
US2783023A (en) * 1950-04-05 1957-02-26 Stalker Dev Company Fluid rotor having damping means
US2823889A (en) * 1950-04-05 1958-02-18 Stalker Dev Company Rotor construction and fabrication
US3083446A (en) * 1950-06-14 1963-04-02 Stalker Corp Rotor construction
US2772851A (en) * 1950-06-14 1956-12-04 Stalker Dev Company Rotor construction
US2849209A (en) * 1950-10-11 1958-08-26 Gen Electric Nozzle construction for turbines
US2642263A (en) * 1951-01-05 1953-06-16 Westinghouse Electric Corp Blade apparatus
US2762114A (en) * 1951-08-28 1956-09-11 Gen Motors Corp Method of making sheet metal turbine bucket
US3027138A (en) * 1951-12-10 1962-03-27 Power Jets Res & Dev Ltd Turbine blades
US2976014A (en) * 1952-01-19 1961-03-21 Bbc Brown Boveri & Cie Blading for use in axial flow machines
US2708564A (en) * 1952-02-29 1955-05-17 Westinghouse Electric Corp Turbine apparatus
US3045967A (en) * 1952-04-12 1962-07-24 Stalker Corp Hollow blades and manufacture thereof
US2863633A (en) * 1952-04-19 1958-12-09 Stalker Dev Company Hollow blades and manufacture thereof
US2801073A (en) * 1952-06-30 1957-07-30 United Aircraft Corp Hollow sheet metal blade or vane construction
US2809802A (en) * 1952-09-10 1957-10-15 Gen Electric Damping turbine blades
US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
US2954208A (en) * 1953-01-09 1960-09-27 Gen Motors Corp Air foil section
US2875948A (en) * 1953-01-19 1959-03-03 Stalker Dev Company Thin wall bladed wheels for axial flow machines
US2719294A (en) * 1953-02-17 1955-10-04 Wilson Jones Co Staple gun tacker
US2859011A (en) * 1953-07-27 1958-11-04 Gen Motors Corp Turbine bucket and liner
US2828940A (en) * 1953-12-30 1958-04-01 United Aircraft Corp Cooled turbine blade
US2869611A (en) * 1955-03-18 1959-01-20 Stalker Dev Company Apparatus including a female die receiving a reciprocating articulated male die for stretch-forming hollow blades
US2916808A (en) * 1955-03-28 1959-12-15 Gen Electric Method of making a blade for turbomachines
US3010696A (en) * 1955-09-26 1961-11-28 Rolls Royce Bladed rotor with means to supply fluid to passages in the blades
US2979809A (en) * 1956-03-14 1961-04-18 Napier & Son Ltd Method of making hollow turbine blades
US3002265A (en) * 1957-02-14 1961-10-03 Stalker Corp Fabrication of blades for compressors and the like
US3039739A (en) * 1958-11-28 1962-06-19 Gen Motors Corp Pinned blade connecting means
US3023998A (en) * 1959-03-13 1962-03-06 Jr Walter H Sanderson Rotor blade retaining device
US3388888A (en) * 1966-09-14 1968-06-18 Gen Electric Cooled turbine nozzle for high temperature turbine
US3747182A (en) * 1970-05-07 1973-07-24 United Aircraft Corp Method of fabricating a hollow turbine blade having an insert therein
US3697192A (en) * 1970-05-07 1972-10-10 United Aircraft Corp Hollow turbine blade
US4037990A (en) * 1976-06-01 1977-07-26 General Electric Company Composite turbomachinery rotor
US5022824A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pinned airfoil propeller blade
US5022825A (en) * 1988-10-07 1991-06-11 United Technologies Corporation Pitch retention member
US5102300A (en) * 1988-10-07 1992-04-07 United Technologies Corporation Pinned airfoil propeller assembly
US5205714A (en) * 1990-07-30 1993-04-27 General Electric Company Aircraft fan blade damping apparatus
US6283707B1 (en) * 1999-03-19 2001-09-04 Rolls-Royce Plc Aerofoil blade damper
GB2347975B (en) * 1999-03-19 2003-01-22 Rolls Royce Plc Aerofoil blade damper
JP2013072333A (ja) * 2011-09-27 2013-04-22 Mitsubishi Heavy Ind Ltd 静翼及び蒸気タービン

Also Published As

Publication number Publication date
DE855178C (de) 1952-11-10
IT454293A (ja)
GB664938A (en) 1952-01-16
FR965814A (ja) 1950-09-22

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