US3055633A - Hot gas turbines - Google Patents

Hot gas turbines Download PDF

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Publication number
US3055633A
US3055633A US728378A US72837858A US3055633A US 3055633 A US3055633 A US 3055633A US 728378 A US728378 A US 728378A US 72837858 A US72837858 A US 72837858A US 3055633 A US3055633 A US 3055633A
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Prior art keywords
blades
spacers
blade
discs
turbine
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Expired - Lifetime
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US728378A
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English (en)
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Pouit Robert
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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
    • 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
    • F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
    • 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
    • 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
    • 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
    • F01D5/186—Film 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings
    • 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

Definitions

  • the present invention relates to turbines operated by a hot gaseous fluid which may result in particular from a vaporization or from a combustion.
  • the invention is more especially but not exclusively concerned with reaction turbines.
  • the chief object of my invention is to provide a turbine of the above mentioned kind which is better adapted to meet the requirements of practice than those known at the present time, in particular concerning the thermal and mechanical behaviour of their blades at the temperature existing during operation of the turbine.
  • the turbine rotor comprises, in combination, a wheel body including two adjacent discs, said discs having respective rim portions which form peripheral jaws and are provided with radial slots, a multiplicity of turbine blades, the root portions of said blades including inclined heels engaged under said disc jaws, a multiplicity of spacers interposed between said root portions of said blades, said blade root portions and said spacers being of complementary shapes, said spacers including inclined heels engaged under said disc jaws, and tightening means for keeping said discs applied against each other in the axial direction and at the same time resiliently holding said blade root portions and said spacers applied against one another in the circumferential direction.
  • FIG. l is a cross-section through a portion of the rim of a turbine rotor substantially on the line II of FIG. 3;
  • FIG. 2 is a similar cross-section on the line II-II of FIG, 3;
  • FIG. 3 is a developed plan view of the blades
  • FIG. 4 is an enlarged view of the top portion of one of the blades in side elevation
  • FIG. 5 is an enlarged view of a part of FIG. 3;
  • FIG. 6 is a cross-section through the rim of a modified form.
  • FIG. 7 is a plan view of the blades of FIG. 6, partly in section.
  • the following description relates to the case of an axial turbine in which the degree of reaction is high and which is driven by a gas at high temperature.
  • the rotor of this turbine is constituted by a turbine wheel 1 supporting a plurality of blades 2 and this rotor is placed in a stator 3, where it is driven by a stream of hot gases indicated by arrows f (FIGS. 1 and 2).
  • a stream of hot gases indicated by arrows f (FIGS. 1 and 2).
  • the portion of each blade located upstream with respect to the stream of gas will be called front portion and that located downstream will be called rear portion.
  • the turbine includes means for producing a laminar flow of cooling gas at high velocity, substantially parallel to the direction of flow of the power gases, along only the rear portion of the blades, that is to say where there is a high reaction, and consequently a high acceleration of the power gases, and other protection means are provided on the front portion of the blades.
  • these last mentioned means are constituted by a sheet or jacket of a refractory material which is a bad conductor of heat, such as nickel or a nickel alloy containing for instance some amount of chromium.
  • this sheet is disposed at a small distance from the surface of the blades and cooling air is made to circulate at low speed in the interval.
  • the edges of said sheet are arranged so as to limit, with the surface of the blade, a slot through which said cooling air escapes laterally and thus to produce the laminar gaseous flow intended to cool the rear portion of the blade.
  • a cooling fluid may also be made to flow through the inside of each blade, and the walls of said blade may be coated with a metallic layer adhering to the surface thereof and made of a material which is a bad conductor of heat.
  • blades 2 are made of a metal preferably having a high thermal conduction such as sintered aluminium or a sintered aluminium alloy.
  • Said blades include root portions 4a and 4b engaged in jaws 5a and 5b which, in the embodiment of FIGS. 1 to 5, are carried by two discs 1a and 1b assembled in any suitable manner, for instance by screws 6 cooperating with tubular nuts 6a, the whole of said discs 1a and 1b constituting the wheel body 1.
  • the front portion of each blade is designated by 2a an the rear portion by 2b, this rear portion being connected with the root portion 4b by a flat wall 7 substantially at right angles to the radial generatrices 7a of blade 2.
  • interval 8 extending from the top of the blade.
  • root portion 2c common to both of these portions 2a and 2b, with a hole 10 therein opening into interval 8.
  • each blade is surrounded by a sheet 11 the rear edges 11a and 11b of which are located slightly beyond the front part of the rear portion 2b of the blade. Between these edges and said blade rear portion, there is left a small interval for the distribution, on the walls of said rear portion, of laminar air films, the air of these films coming from interval 8 as wil be more fully explained hereinafter.
  • the front portion 2a of the blade which is already protected both by a thin deposit 34 (FIG. 5) of a material which is a bad conductor of heat and by sheet 11 itself (also made of a material which is a bad conductor of heat) is further protected by thin sheets of air circulating between the wall of the front portion 2a and the inner wall of sheet 11.
  • I provide, in the body of the front portion of the blade, recesses such as 12, 13, 14, and 15 forming, with sheet 11, passages extending in the radial direction. Some of these recesses (13, 14) open radially and others (12, 15) laterally in the direction of flow of the power gases into a notch such as 12a provided in sheet 11. At least some of these recesses may have throttled portions such as 16 for adjusting the velocity of flow of the cooling air.
  • the distance between the bottom of the recesses and the sheet and the velocity of the air flowing between these two elements are chosen in such manner that the flow is laminar.
  • I may provide, in each of the portions 2a and 2b of the blades, radial channels such as 17 and 18 through which cooling air is made to flow so as to dissipate the heat which penetrates into the blades despite the above described precautions.
  • the cooling air of each blade is collected from an annular space 19 extending along the periphery of wheel body 1 and to which air is fed through radial channels 20 from a source under pressure, the air in said chamber 19 being further compressed by the action of the centrifugal force. From this chamber 19, air flows:
  • rim 25 and spring 27 are provided with holes 25a, 25b and 27a, 27b, 270 so as to permit evacuation of the cooling air.
  • rim 25 bears against the ends of the blades on which it is tightly applied for instance by hooping at high temperature and, in order to permit the outflow of the cooling fluid which has flown through the channels 18 provided in the rear portion of the blades, said channels are arranged to open into the outer rear walls 35a of the blades through slots 35.
  • the holes 25a are directed in such manner as to project, in the form of a whirling ring, into the annular space existing between the rotor and the stator, the cooling fluid which has flown through the channels 35b provided in the front portion of the blades.
  • spacers 28 are given a shape complementary of that of the blade roots, so that they fit between them. and form therewith an outer gas-tight wall for annular chamber 19.
  • These spacers 28 include heels 29a and 29b of a cross-section identical to that of the heels 4a and 4b of the blades and the surfaces of contact between said heels and the jaws 5a and 5b of the wheel body are inclined in such manner that the tightening effort exerted by screws 6 produces a centripetal thrust on the blade root portions and the spacers which tends to assemble them tightly against one another.
  • the tight engagement is made possible by the fact that the distance (FIG. 2) between the ends 5' of the inclined faces of the jaws furthest from the central plane of the rotor is greater than the distance between the outer ends 4 of the heels.
  • the peripheral portions of discs 1a and 1b are provided with radial slots 36 (FIGS. 1 and 2) which extend at least from the roots 5 of the jaws (FIG. 2) to the outer peripheries of the disc.
  • sheets 11, subjected to the action of the centrifugal force are held at their inner ends by being caught over most of the periphery thereof between the blade root portions and the spacers.
  • the section of the root portions of the blades corresponds substantially to the section of said blades over at least most of the distance along which sheets 11 are applied, I may however provide on the roots of the blades local reinforcements 30 (FIG. 5 such that the spacers 28 fit against them, and fold sheet 11 at these places so as to have it held against the radial side of said reinforcement.
  • sheets 11 may be maintained on the blades by bent portions such as 11c (FIG. 5) engaged in recesses such as the outlets of conduits 17 and/or by pins 31, preferably resilient pins, for wedging small tongues cut from the sheets in suitable housings 31a.
  • bent portions such as 11c (FIG. 5) engaged in recesses such as the outlets of conduits 17 and/or by pins 31, preferably resilient pins, for wedging small tongues cut from the sheets in suitable housings 31a.
  • spacers 28 may be protected by sheets 32 of a material which is a bad conductor of heat, such as nickel or a nickel alloy containing for instance some amount of chromium. These sheets 32 are engaged at the same time as heels 29a and 2% by the jaws 5a and 5b of discs 1a and 1b.
  • these sheets 32 are bearing on marginal ribs 33 of the spacers (FIG. 1) so as to provide insulating air cushions between the external surfaces of spacers 28 and sheets 32.
  • jaws 5a and 5b and slots 36 are provided directly in discs 1a and 1b, they are provided in plates 37a and 37b fixed on discs in and 1b, as shown on the drawing, by means of the above mentioned screws 6 and nuts 6a, jaws 5a and 5b belonging to the rim portions 38a and 38b of plates 37a and 37b.
  • Said rim portions 38a and 3812 are given such a volume and such an outwardly oifset shape that the centrifugal force, indicated by arrow F on FIG. 6, applied during r0 tation of the turbine to the masses constituted by the portions of the rim located between slots 36, is offset with respect to the section of metal connecting said masses with plates 37a and 37b, whereby there is created in said sections a bending torque due to the reaction exerted by heels 4a and 4b under the effect of the centrifugal force exerted on blades 2 and on spacers 28, so as to keep in operation at high temperature at least the same tight fixation of the blades as when the turbine is at rest in the cold state.
  • FIGS. 1 to 5 which does not includes plates 37a and 37b.
  • the blades and also the discs 1a and 1b that support them are made of a light alloy the mechanical characteristics of which deteriorate very quickly when the temperature rises, it seems preferable to have recourse to separate plates such as 37a and 37b made of special spring steel which is less responsive to variations under the effect of the temperature, these plates forming a thermal protection screen between the usual distributor of the turbine and the heels of the blades.
  • a stream of cooling fluid is made to pass under sheets 32.
  • said sheets which cover both the root portions 9 of the blades and spacers 28, are folded a first time to be caught between heel 4a and jaw 5a, or heel 4b and jaw 5b, thus forming a chamber 39 along one side of the blades, and a second time to be caught between heel 4a or 4b, and the periphery of the corresponding disc 1a or 1b on which said heel is applied by the pressure exerted on the blades.
  • plates 32 assume a convex shape which moves them apart from the outer wall of the blades root portions against which they are applied in the cold state.
  • I provide in spacers 38 grooves 40 which may be placed in communication with the channels for the circulation of the cooling fluid as above described.
  • the turbine when the turbine is provided with means for supplying, on the upstream side of the wheel body 1, a cooling fluid, such means being represented on FIG. 5 by a fixed chamber 41 adapted to be fed with fluid under pressure and closed by labyrinth sealing means 42, the leaks through this labyrinth sealing means are used to circulate the cooling fluid through the above mentioned space.
  • a cooling fluid such means being represented on FIG. 5 by a fixed chamber 41 adapted to be fed with fluid under pressure and closed by labyrinth sealing means 42
  • the leaks through this labyrinth sealing means are used to circulate the cooling fluid through the above mentioned space.
  • I provide in sheet 32, opposite chambers 39, inlet slots 43 and outlet slots 44.
  • I may provide in disc 1b divergent channels 20 so as to re-circulate the fluid leaks which have already circulated under sheets 32.
  • I further provide a flange 46 fixed on at least one of the discs 1a and 1b to support the root portions 9 of the blades 2 and the spacers 28 with respect to said discs.
  • Said flange 46 may be provided with projections 47 which serve to center and to drive the blades and spacers.
  • the inner edges of sheets 11 may be folded on the root portions 9 of the blades and caught between said root portions and flange 46.
  • Turbine wheels obtained according to my invention have their blades efliciently protected against the heat of the power gases and said blades are always resiliently mounted without play on their support with a tension which may be either constant or increasing together with the speed of rotation, whatever he the difference of expansion, in operation, under different thermal conditions.
  • a rotor which comprises, in combination, a wheel body including two adjacent discs of resilient material, said discs having respective rim portions provided with flanges which form peripheral jaws with inclined faces directed towards the axis and provided with radial slots extending at least from the roots of the jaws to the outer perimeter of the wheel, a plurality of turbine blades, the root portions of said blades including complementarily inclined heels engaged under the inclined faces of said disc jaws, a plurality of spacers interposed between said root portions of said blades, said blade root portions and said spacers being of complementary shapes at their juxtaposed sides, said spacers including complementarily inclined heels engaged under the inclined faces of said disc jaws, the distance between the ends of the inclined faces of the jaws furthest from the central plane of the rotor being greater than the distance between the outer ends of the heels, and tightening means operatively engaging the discs drawing said discs towards each other in the axial direction, thereby exerting an inward radial pressure on the
  • a turbine rotor according to claim 1 in which said rim portions of said discs are integral therewith.
  • a turbine rotor according to claim 1 in which said discs include plates fixed thereto, said rim portions being integral with said plates.
  • a turbine rotor according to claim 1 further in cluding a sheet of a refractory material disposed at a short distance from at least a portion of each of said blades, the inner edge of said sheet being clamped between the root portion of said blade and the spacers adjoining it.
  • a turbine rotor according to claim 1 further including a sheet of a refractory material covering at least a portion of each of said blades, at a small distance therefrom, and means for circulating a cooling fluid through the space between said blade and said sheet.
  • a turbine rotor according to claim 5 in which said sheet covers only the front portion of said blade, whereby a laminar gaseous flow escaping from said space runs along the rear portion of said blade.
  • a turbine rotor according to claim 1 in which the portions of said discs located between said radial slots form masses resiliently carried by the disc bodies and having respective gravity centers such that the centrifugal force applied to each of said masses when the turbine is running applies the heel portions of said masses against the heels of said spacers and of said blade root portion.
  • a turbine rotor according to claim 1 further includ ing sheets of a refractory material covering the outer surfaces of said spacers at a small distance therefrom and caught between the jaws of said discs and the heels of said spacers.
  • a turbine rotor according to claim 1 further including sheets of a refractory material covering, at a small distance therefrom, the outer surfaces of said spacers and of the root portions of said blades, said sheets being caught between, on the one hand, the jaws of said discs and, on the other hand, the heels of said spacers and those of said blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US728378A 1957-04-19 1958-04-14 Hot gas turbines Expired - Lifetime US3055633A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR736892A FR1245518A (fr) 1957-04-19 1957-04-19 Perfectionnements apportés aux turbines à fluide gazeux chaud
FR755915A FR75183E (de) 1957-04-19 1958-01-15

Publications (1)

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US3055633A true US3055633A (en) 1962-09-25

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US728378A Expired - Lifetime US3055633A (en) 1957-04-19 1958-04-14 Hot gas turbines

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US (1) US3055633A (de)
CH (1) CH370596A (de)
DE (1) DE1223623B (de)
FR (2) FR1245518A (de)
GB (1) GB878367A (de)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3746469A (en) * 1971-03-03 1973-07-17 Gen Motors Corp Turbomachine rotor
US4051585A (en) * 1976-07-26 1977-10-04 United Technologies Corporation Method of forming a turbine rotor
US4453890A (en) * 1981-06-18 1984-06-12 General Electric Company Blading system for a gas turbine engine
WO1994011616A1 (de) * 1992-11-19 1994-05-26 Bmw Rolls-Royce Gmbh Kühlung des deckbandes einer turbinenschaufel
US5476364A (en) * 1992-10-27 1995-12-19 United Technologies Corporation Tip seal and anti-contamination for turbine blades
EP2236757A3 (de) * 2009-03-17 2013-10-23 United Technologies Corporation Geteilte Rotorscheibenanordnung für ein Gasturbinentriebwerk
US20140219806A1 (en) * 2011-10-20 2014-08-07 Mitsubishi Hitachi Power Systems, Ltd. Rotor blade support structure
US20200063577A1 (en) * 2018-08-22 2020-02-27 Rolls-Royce Plc Turbine wheel assembly
US20210222558A1 (en) * 2020-01-17 2021-07-22 United Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment
US11208892B2 (en) 2020-01-17 2021-12-28 Raytheon Technologies Corporation Rotor assembly with multiple rotor disks
US11339673B2 (en) 2020-01-17 2022-05-24 Raytheon Technologies Corporation Rotor assembly with internal vanes
US11371351B2 (en) * 2020-01-17 2022-06-28 Raytheon Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment
US11401814B2 (en) 2020-01-17 2022-08-02 Raytheon Technologies Corporation Rotor assembly with internal vanes
US20230167745A1 (en) * 2021-11-26 2023-06-01 Ge Avio S.R.L Gas turbine engine including a rotating blade assembly
US12000308B2 (en) 2022-08-23 2024-06-04 General Electric Company Rotor blade assemblies for turbine engines

Families Citing this family (3)

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Publication number Priority date Publication date Assignee Title
FR2108141B1 (de) * 1970-06-23 1973-11-23 Trefimetaux
FR2661944B1 (fr) * 1990-05-14 1994-06-10 Alsthom Gec Etage de turbomachine avec pertes secondaires reduites.
CN113623014B (zh) * 2021-07-22 2023-04-14 西安交通大学 一种燃气轮机透平叶片-轮盘联合冷却结构

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US905487A (en) * 1907-05-16 1908-12-01 Gen Electric Bucket-wheel for turbines.
US1008758A (en) * 1910-08-03 1911-11-14 Gen Electric Space-block for turbines.
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US1178452A (en) * 1913-10-01 1916-04-04 Terry Steam Turbine Company Turbine-blading.
US1362074A (en) * 1919-05-03 1920-12-14 British Westinghouse Electric Turbine
CH124821A (de) * 1926-11-06 1928-03-01 Alfred Buechi Schaufelung für Gas- und Dampfturbinen.
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US2401826A (en) * 1941-11-21 1946-06-11 Dehavilland Aircraft Turbine
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US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade
US2623727A (en) * 1945-04-27 1952-12-30 Power Jets Res & Dev Ltd Rotor structure for turbines and compressors
US2696364A (en) * 1948-07-08 1954-12-07 Thompson Prod Inc Turbine bucket
US2780435A (en) * 1953-01-12 1957-02-05 Jackson Thomas Woodrow Turbine blade cooling structure
US2810544A (en) * 1951-01-20 1957-10-22 Maschf Augsburg Nuernberg Ag Gas turbine rotor
US2828940A (en) * 1953-12-30 1958-04-01 United Aircraft Corp Cooled turbine blade

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DE68359C (de) * C. G. P. DE LAVAL, Dr. phil., in Stockholm In den Radkörper geklemmte Schaufeln für Dampf- oder Gasturbinen
DE735184C (de) * 1941-03-11 1943-05-07 Maschf Augsburg Nuernberg Ag Gasturbinenlaeufer, bei welchem Schaufeln und Laeufer aus keramischen Massen hergestellt sind
DE862231C (de) * 1941-10-09 1953-01-08 Bayerische Motoren Werke Ag Mehrteiliges Turbinenlaufrad, insbesondere fuer Abgasturbinen
FR960069A (de) * 1947-04-02 1950-04-12
DE814545C (de) * 1949-04-29 1951-09-24 Ruston & Hornsby Ltd Mehrstufiger Laeufer fuer Axialturbinen, insbesondere Gasturbinen
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GB710119A (en) * 1951-08-27 1954-06-09 Rolls Royce Improvements in or relating to turbines and compressors and the like machines
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Publication number Priority date Publication date Assignee Title
DE554119C (de) * 1932-07-13 Alfred Buechi Dipl Ing Nachgiebige Schaufelbefestigung fuer Gas- und Dampfturbinen
US768597A (en) * 1902-08-21 1904-08-30 Gen Electric Turbine-bucket.
US905487A (en) * 1907-05-16 1908-12-01 Gen Electric Bucket-wheel for turbines.
US1008758A (en) * 1910-08-03 1911-11-14 Gen Electric Space-block for turbines.
US1178452A (en) * 1913-10-01 1916-04-04 Terry Steam Turbine Company Turbine-blading.
US1118361A (en) * 1914-06-19 1914-11-24 Gen Electric Wheel for elastic-fluid turbines.
US1362074A (en) * 1919-05-03 1920-12-14 British Westinghouse Electric Turbine
CH124821A (de) * 1926-11-06 1928-03-01 Alfred Buechi Schaufelung für Gas- und Dampfturbinen.
US2401826A (en) * 1941-11-21 1946-06-11 Dehavilland Aircraft Turbine
US2623727A (en) * 1945-04-27 1952-12-30 Power Jets Res & Dev Ltd Rotor structure for turbines and compressors
US2501038A (en) * 1947-03-29 1950-03-21 United Aircraft Corp Mounting for hollow turbine blades
US2696364A (en) * 1948-07-08 1954-12-07 Thompson Prod Inc Turbine bucket
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade
US2810544A (en) * 1951-01-20 1957-10-22 Maschf Augsburg Nuernberg Ag Gas turbine rotor
US2780435A (en) * 1953-01-12 1957-02-05 Jackson Thomas Woodrow Turbine blade cooling structure
US2828940A (en) * 1953-12-30 1958-04-01 United Aircraft Corp Cooled turbine blade

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3746469A (en) * 1971-03-03 1973-07-17 Gen Motors Corp Turbomachine rotor
US4051585A (en) * 1976-07-26 1977-10-04 United Technologies Corporation Method of forming a turbine rotor
US4453890A (en) * 1981-06-18 1984-06-12 General Electric Company Blading system for a gas turbine engine
US5476364A (en) * 1992-10-27 1995-12-19 United Technologies Corporation Tip seal and anti-contamination for turbine blades
WO1994011616A1 (de) * 1992-11-19 1994-05-26 Bmw Rolls-Royce Gmbh Kühlung des deckbandes einer turbinenschaufel
EP2236757A3 (de) * 2009-03-17 2013-10-23 United Technologies Corporation Geteilte Rotorscheibenanordnung für ein Gasturbinentriebwerk
US20140219806A1 (en) * 2011-10-20 2014-08-07 Mitsubishi Hitachi Power Systems, Ltd. Rotor blade support structure
US9677406B2 (en) * 2011-10-20 2017-06-13 Mitsubishi Hitachi Power Systems, Ltd. Rotor blade support structure
US20200063577A1 (en) * 2018-08-22 2020-02-27 Rolls-Royce Plc Turbine wheel assembly
US10934862B2 (en) * 2018-08-22 2021-03-02 Rolls-Royce Plc Turbine wheel assembly
US20210222558A1 (en) * 2020-01-17 2021-07-22 United Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment
US11208892B2 (en) 2020-01-17 2021-12-28 Raytheon Technologies Corporation Rotor assembly with multiple rotor disks
US11286781B2 (en) * 2020-01-17 2022-03-29 Raytheon Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment
US11339673B2 (en) 2020-01-17 2022-05-24 Raytheon Technologies Corporation Rotor assembly with internal vanes
US11371351B2 (en) * 2020-01-17 2022-06-28 Raytheon Technologies Corporation Multi-disk bladed rotor assembly for rotational equipment
US11401814B2 (en) 2020-01-17 2022-08-02 Raytheon Technologies Corporation Rotor assembly with internal vanes
US20230167745A1 (en) * 2021-11-26 2023-06-01 Ge Avio S.R.L Gas turbine engine including a rotating blade assembly
US12000308B2 (en) 2022-08-23 2024-06-04 General Electric Company Rotor blade assemblies for turbine engines

Also Published As

Publication number Publication date
FR1245518A (fr) 1960-11-10
FR75183E (de) 1961-09-08
DE1223623B (de) 1966-08-25
CH370596A (fr) 1963-07-15
GB878367A (en) 1961-09-27

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