Blade Inserts Patents (Class 416/96A)
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Patent number: 5073083Abstract: A vane for a turbojet engine, is disclosed having an airfoil-shaped body with a leading edge, a trailing edge, a generally concave sidewall and a generally convex sidewall defining a hollow vane interior. A cooling air supply duct extends substantially over the entire length of the vane and communicates with a turbulence chamber in the vicinity of the leading edge which is separated from the supply duct by a partition having air cooling orifices to allow the air to pass from the cooling air supply duct into the turbulence chamber. The air from the turbulence chamber is evacuated through evacuation orifices defined by the generally convex sidewall in the vicinity of the leading edge. A plurality of heat exchange members are located in the interior of the vane such that they are spaced apart, extend substantially parallel to each other and substantially perpendicular to a longitudinal axis of the vane.Type: GrantFiled: March 6, 1991Date of Patent: December 17, 1991Assignee: Societe Nationale d'Etude de Construction de Moteurs d'AviationInventor: Benoit P. Guyon
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Patent number: 5027604Abstract: A hot gas overheat protection device is provided for gas turbine engines and the like. An outer metal wall having cooling air supplied through cooling holes therethrough from the outside is shielded from hot gas flow by the provision of highly temperature resistant lining wall elements spaced from the metal wall. A thin metal skin is provided between the metal wall and the wall elements defining intermediate spaces communicating with cooling air ports in the metal wall. The thin metal skin has a melting point equal to or lower than that of the metal wall so as to provide for fusion or rupture of the thin metal skin in the event the insulating wall elements are locally ruptured, whereby the cooling air is provided through the cooling air ports in a direction against the flow of hot gases to thereby mitigate the effects of the rupture and protect the metal wall.Type: GrantFiled: January 3, 1989Date of Patent: July 2, 1991Assignee: MTU Motoren- und Turbinen Union Munchen GmbHInventor: Wolfgang Krueger
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Patent number: 5022817Abstract: A gas turbine engine is provided with hollow guide vanes having thermally responsive actuators mounted within each for individually controlling the cooling air flow therethrough in response to local temperature variations.Type: GrantFiled: September 12, 1989Date of Patent: June 11, 1991Assignee: Allied-Signal Inc.Inventor: Bernard O'Halloran
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Patent number: 5002460Abstract: An airfoil blade includes an airfoil body with a coolant passageway having a centerline which is generally straight and generally parallel to the longitudinal axis of the airfoil body for directing coolant flow in a generally longitudinal direction. An insert is placed within the coolant passageway for imparting rotation to the longitudinal directed coolant flow such that the longitudinal directed coolant flow rotates at least one complete turn about a spin axis which is generally parallel to the centerline of the coolant passageway. In another embodiment of this invention, the passageway is twisted along its length to rotate the longitudinally directed coolant flow at least one complete turn about the spin axis to increase the heat transfer coefficient.Type: GrantFiled: October 2, 1989Date of Patent: March 26, 1991Assignee: General Electric CompanyInventors: Ching-Pang Lee, Robert O. Brooks
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Patent number: 4992026Abstract: A blade of a gas turbine includes a main body having a dovetail portion and a blade portion extending from the dovetail portion. A cooling air passage for flowing a cooling air is formed in the main body to cool the blade portion. The passage includes a cooling air inlet port open to the dovetail portion and an outlet port open to an extended tip of the blade portion. A first passage portion extends from the inlet port to the portion close to the extended tip along a leading edge of the blade portion. A final passage portion extends from the dovetail portion to the outlet port. The flow sectional area of the final passage portion is gradually decreased from the dovetail portion toward the outlet port. The final passage portion communicates with a number of film cooling holes which are open to the suction side surface of the blade portion.Type: GrantFiled: June 22, 1989Date of Patent: February 12, 1991Assignee: Kabushiki Kaisha ToshibaInventors: Fumio Ohtomo, Yasuo Okamoto, Shoko Ito, Yoshitaka Fukuyama, Hideo Iwasaki, Takeshi Watanabe
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Patent number: 4962640Abstract: An apparatus and method are provided for preventing the plugging of cooling air distribution holes in a hollow gas turbine vane by particles entrained in the cooling air. The portion of the cooling air is bled from the vane and discharged into the hot gas downstream of the vane, the shunted bleed air carrying the entrained particles.Type: GrantFiled: February 6, 1989Date of Patent: October 16, 1990Assignee: Westinghouse Electric Corp.Inventor: Edward W. Tobery
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Patent number: 4946346Abstract: A gas turbine vane has a vane airfoil defining a cavity extending along the longitudinal direction of the vane airfoil. A guide cylinder is disposed in the cavity to guide coolant fluid supplied from an external source thereof. A plurality of flowing holes are concentrated substantially centrally with respect to the vane airfoil in the longitudinal direction.Type: GrantFiled: September 23, 1988Date of Patent: August 7, 1990Assignee: Kabushiki Kaisha ToshibaInventor: Syoko Ito
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Patent number: 4897020Abstract: A nozzle guidevane for a gase turbine engine 10 comprising a first fixed upstream portion 24, a movable downstream portion 26 and a seal situated therebetween. The seal comprises two pairs of ridges 56, 58 on the upstream portion and two ridges 60 on the downstream portion 26 which co-operate with each other to form a flow restrictor which maintains the flow of escaping air within acceptable limits. The air which does escape is used to advantage by maintaining the mainflow of air over the outside of the vane 22.Type: GrantFiled: May 8, 1989Date of Patent: January 30, 1990Assignee: Rolls-Royce plcInventor: Robert C. Tonks
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Patent number: 4840538Abstract: A device for cooling the salient-type rotor of electrical machines in which interpolar bodies are placed between and parallel to the salient poles of a rotor creating narrow channels between the salient poles and the interpolar bodies, to effectively cool the salient poles by the cooling air blowing radially through the channels between the interpolar body and the salient poles, and the interpolar bodies having circumferentially extending top surface close to the internal surface of stator creating a circumferential channel between the interpolar body and the internal surface of stator, bridging the gap between the salient poles to reduce turbulences and energy losses created by the rotation of the rotor.Type: GrantFiled: August 18, 1987Date of Patent: June 20, 1989Inventor: Kalman N. Lehoczky
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Patent number: 4798515Abstract: The cooling insert for a movable vane in a jet engine is divided into plural overlapping forward and aft segregated members, each member being coolant fed through separate vane trunnion areas and each insert is of successively decreasing cross-sectional area. Problems of locally inadequate vane cooling, coolant match point movement, and unequal coolant supply pressures are addressed by the disclosed apparatus. Reuse of the trunnion supplied impingement cooling air for additional cooling functions is also disclosed.Type: GrantFiled: May 19, 1986Date of Patent: January 17, 1989Assignee: The United States of America as represented by the Secretary of the Air ForceInventors: Edward S. Hsia, John H. Starkweather, William K. Koffel
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Patent number: 4790721Abstract: An airfoil-shaped blade assembly having a metallic core, thin coolant liner and ceramic blade jacket includes variable-size cooling passages and a circumferential stagnant air gap to provide a substantially cooler core temperature during high temperature operations.Type: GrantFiled: April 25, 1988Date of Patent: December 13, 1988Assignee: Rockwell International CorporationInventors: Donald H. Morris, Daniel M. Shea
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Patent number: 4759688Abstract: Method and apparatus for delivering cooling fluid flow to the internal blade cooling passages in a gas turbine engine, wherein cooling flow is injected into a radial side face of the hub of the turbine wheel and is ported therefrom through internal passages in the hub to the blade internal cooling passages.Type: GrantFiled: December 16, 1986Date of Patent: July 26, 1988Assignee: Allied-Signal Inc.Inventors: E. Scott Wright, Chester L. Henry
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Patent number: 4697985Abstract: A gas turbine vane generally comprises an outer hollow vane member provided with a plurality of ribs aligned on the inner wall of the outer vane member and an insertion member of vane shape inserted into the outer hollow vane member so as to rigidly engage with the ribs. A turbulence chamber is defined between the leading edge portions of the outer and inner vane members, and the inner hollow insertion member is provided with numerous orifices at its leading edge portion for injecting cooling fluid into this turbulence chamber. A plurality of cooling passages operatively connected to the turbulence chamber are formed between the flank walls of the outer and inner vane members, and a plurality of orifices are further provided through the flank walls of the inner insertion member so as to communicate the interior thereof with the cooling passages.Type: GrantFiled: March 6, 1985Date of Patent: October 6, 1987Assignee: Kabushiki Kaisha ToshibaInventor: Isamu Suzuki
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Patent number: 4684322Abstract: The blade has an aerofoil body 10 having a leading edge surface 11 which is cooled by air passing through a helical first passage 12 having first portions passing close to said leading edge surface and alternating with second portions passing through a more nearly central part of the blade section remote from said leading edge. A spanwise but straight second passage 15 extends through the blade in a position within the helical passage and closer to the second than the first portions thereof. Heat abstracted from the leading edge by air flow in said first portions is transferred by the flow to the second portions and from there through the blade material to the flow in the straight passage.Type: GrantFiled: October 26, 1982Date of Patent: August 4, 1987Assignee: Rolls-Royce plcInventors: Rodney J. Clifford, Ian J. Charters
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Patent number: 4666368Abstract: Cooling air from turbine nozzle vanes of a hot gas turbine engine is collected from the vanes by an air connector. A conduit connects to the connector and terminates adjacent a turbine wheel so that air flows through the vanes and through the conduit to be emitted from the end thereof in a jet stream directed against the turbine wheel. A vaned swirl nozzle is inserted in the conduit and adjacent a turbine wheel to impart a turning impetus to the air flow stream being emitted from the nipple. The emitted air stream is then directed tangentially against or adjacent the turbine wheel in the direction of rotation thereof.Type: GrantFiled: May 1, 1986Date of Patent: May 19, 1987Assignee: General Electric CompanyInventors: Richard B. Hook, Jr., Richard D. Montanye
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Patent number: 4650399Abstract: A rotor blade 14 having a spar 138 and shell 134 is disclosed. Various construction details are developed for efficiently transferring rotational loads on the rotor blade to the root section 28 of the spar. The spar has a projection 139 over which extends a portion 100 of the shell and a platform 36 of the rotor blade.Type: GrantFiled: May 7, 1984Date of Patent: March 17, 1987Assignee: United Technologies CorporationInventors: Harold M. Craig, Ernest Feder
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Patent number: 4645421Abstract: A hybrid blade for a fluid flow engine has a U-shaped core of metal or a metal alloy and a ceramic outer jacket which forms together with a mounting plate a unitary, single piece structure. The legs of the core straddle the mounting plate and a heat insulating member is inserted between a crosspiece of the core and the mounting plate. This structure permits relative movement between the core and the jacket to compensate for different heat expansion coefficients.Type: GrantFiled: June 2, 1986Date of Patent: February 24, 1987Assignee: MTU Motoren-und Turbinen-Union Muenchen GmbHInventor: Werner Huether
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Patent number: 4616976Abstract: A cooled vane or blade for a gas turbine engine has a cooling arrangement for its trailing region which can be accommodated in the relatively thin section available. In this arrangement the trailing region of the hollow interior of the blade is divided off from the remainder by a partition which may be apertured to allow cooling air to enter the compartment thus formed. The concave, pressure flank of the compartment is cooled by arrays of film cooling holes while the convex, suction flank has a perforated plate spaced therefrom to provide impingement cooling. The suction flank is therefore unapertured and there is no disturbance of the high speed airflow in this region. The spent impingement air leaves the aerofoil via a slot and may pass over pedestals en route to cool the entire trailing edge.Type: GrantFiled: June 28, 1982Date of Patent: October 14, 1986Assignee: Rolls-Royce plcInventors: Barry W. Lings, John H. Nicholson
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Patent number: 4604780Abstract: Methods for manufacturing components having internal flow passages in which an insert composed of a carrier and passage-forming and/or flow controlling elements is sandwiched between or installed in elements of the component. The insert associated and component elements are then bonded together and the carrier subsequently leached away to complete the formation of the flow passages.Type: GrantFiled: February 3, 1983Date of Patent: August 12, 1986Assignee: Solar Turbines IncorporatedInventor: Arthur G. Metcalfe
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Patent number: 4573872Abstract: A heat resistance structure adapted to be used in a passage of a high temperature fluid, comprises a heat resistant metal plate having a smooth outer surface, a layer of a substance having a high heat transmission resistance extended along an internal surface of the metal plate, and heat conductive bodies provided in close contact with the layer, all being arranged in this order from the outer surface of the structure to the interior of the structure. A plurality of coolant passages are further provided through each of the heat conductive bodies.Type: GrantFiled: October 26, 1983Date of Patent: March 4, 1986Assignee: Tokyo Shibaura Denki Kabushiki KaishaInventor: Yuji Nakata
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Patent number: 4526512Abstract: A flow control body in the aft end of a hollow core of a turbine vane provides localized increased velocity cooling air flow in a wide portion which is otherwise difficult to cool. The flow control body includes lands and grooves with the cooling air being constrained to flow through the grooves and provide localized cooling while conductive heat transfer through the lands to the flow control body provides substantial temperature uniformity along the length of the vane. Turbulence chambers may be formed in the flow control body to further control cooling and the shape or other parameters of the flow control body may be modified to accommodate uneven end-to-end heating of the vane.Type: GrantFiled: March 28, 1983Date of Patent: July 2, 1985Assignee: General Electric Co.Inventor: Richard B. Hook
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Patent number: 4519745Abstract: A ceramic blade assembly including a corrugated-metal partition situated in the space between the ceramic blade element and the post member, which corrugated-metal partition forms a compliant layer for the relief of mechanical stresses in the ceramic blade element during aerodynamic and thermal loading of the blade and which partition also serves as a means for defining contiguous sets of juxtaposed passages situated between the ceramic blade element and the post member, one set being open-ended and adjacent to exterior surfaces of the post member for directing cooling fluid thereover and the second set being adjacent to the interior surfaces of the ceramic blade element and being closed-off for creating stagnant columns of fluid to thereby insulate the ceramic blade element from the cooling air.Type: GrantFiled: July 12, 1982Date of Patent: May 28, 1985Assignee: Rockwell International CorporationInventors: Irwin E. Rosman, Hector S. Bourgeois
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Patent number: 4512069Abstract: A method of manufacturing hollow flow profiles having optimum aerodynamic configurations in conformance with a commensurate application, about the respective outer skin of which there flows a first work medium during operation, such as hot gas, whereas ducts which are arranged within the interior of the flow profiles are concurrently streamed through by a second work medium, such as compressed air. The method of the present invention employs suitable deformation techniques (drawing, circular swaging or rolling) at preselected locations to particularly produce web-like aggregations of material. When appropriate materials are used for this purpose, contoured profiles of that type can also be formed through extruding. The webs, depending upon the demands of preceding or successive process steps, can be formed externally, internally or on both sides of the conduit material.Type: GrantFiled: February 4, 1983Date of Patent: April 23, 1985Assignee: Motoren-und Turbinen-Union Munchen GmbHInventor: Klaus Hagemeister
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Patent number: 4505639Abstract: The present axial-flow turbine blade has two cooling channels extending radially through the blade. These radial channels communicate with each other through impingement cooling ducts or holes (3) extending substantially axially through the blade. One channel (1) supplies cooling fluid through the holes (3) into the other channel (2) which is located nearer the leading edge (8) of the blade and extends substantially in parallel to the leading edge (8). The cooling fluid impacts on the wall of the other channel (2) and is laterally blown out at a side wall of the blade. For optimal cooling, especially of the leading edge of the blade, which is subject to severe thermal loads, this edge is penetrated by cooling elements (4) in the form of pins or wires in axial alignment with the impingement cooling holes or ducts (3). These cooling pins or wires (4) reach into the channel (2) nearer the leading edge with their tapered end (5) and are made of a highly thermally conductive material.Type: GrantFiled: March 21, 1983Date of Patent: March 19, 1985Assignee: MTU Motoren-Und Turbinen-Union Muenchen GmbHInventors: Helmut Groess, Horst Graeml, deceased
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Patent number: 4484859Abstract: In order to damp possible vibration of a rotor blade for a gas turbine engine, the blade has a hollow tip portion with an internal surface extending across the direction of the centrifugal field on the blade. A weight comprising e.g. Silicon Nitride or Carbide is caused by centrifugal force to bear on this surface. Relative motion and hence friction between the weight and the surface serves to damp vibration of the blade.Type: GrantFiled: December 13, 1982Date of Patent: November 27, 1984Assignee: Rolls-Royce LimitedInventors: George Pask, John H. R. Sadler, John F. Coplin
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Patent number: 4482295Abstract: A hollow stator vane for a turbine is provided with separate forward and aft inserts 26 and 32 with the forward insert providing impingement cooling of the vane walls while the aft insert is closely fitted into the vane internal cavity to provide closely defined channel widths between the insert and facing walls of the vane, the aft insert also including means functioning during operation to ensure the maintenance of the closely defined channel widths, the coolant air admitted to the inserts functioning first for impingement cooling, then channel flow cooling along the aft insert, and then channel flow cooling of the trailing edge 18 through an exit slot.Type: GrantFiled: April 8, 1982Date of Patent: November 13, 1984Assignee: Westinghouse Electric Corp.Inventors: William E. North, Thomas M. Szewczuk
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Patent number: 4480956Abstract: A high-temperature, extremely high-speed ceramet composite blade comprising a ceramic blade jacket seated from above on a metallic core having a crossweb near its upper end for securing the jacket on the core by one or more metallic retaining pins extending through the crossweb and secured to the core. A head on each bolt is located within a chamber formed above the cross-web and surrounded by the radially projecting end of the blade jacket. A porous abradable coating is secured to the head of the bolt and substantially fills the chamber. The coating projects slightly beyond the end of the blade jacket and is supplied and permeated with cooling air via a cooling duct extending through the retaining pin and metallic core.Type: GrantFiled: January 26, 1983Date of Patent: November 6, 1984Assignee: Mortoren-und Turbinen-UnionInventors: Wolfgang Kruger, Werner Huther
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Patent number: 4473336Abstract: The present invention relates to turbine blades and in particular to turbine blades for use in gas turbine engines. Tensile stresses are introduced into turbine blades when they rotate at high speeds on a turbine rotor. In order to minimize the stresses in an outer skin of an aerofoil of the turbine blade, the outer skin is secured to a platform and an inner core, and in operation a temperature difference is set up between the outer skin and the inner core. The temperature difference produces a thermal compressive stress in the outer skin which opposes the tensile stress produced due to the rotation of the turbine blade. The extremities of the outer skin may be secured to the platform with either a tensile or compressive prestress depending upon the temperature difference between the outer skin and inner core at normal operating conditions.Type: GrantFiled: September 14, 1982Date of Patent: September 25, 1984Assignee: Rolls-Royce LimitedInventors: Michael H. Coney, Andrew G. Dutton, David A. Richardson
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Patent number: 4461612Abstract: An aerofoil, particularly a nozzle guide vane, for a gas turbine engine comprises a hollow interior with an air guide tube located therein. The air guide tube has apertures therein, and in order to cause the free edges of the apertures to seal against internal ribs of the aerofoil, springs are provided to force the open edges apart. Conveniently the springs comprise straps between the apertures which are formed with a corrugated shape.Type: GrantFiled: April 19, 1983Date of Patent: July 24, 1984Assignee: Rolls-Royce LimitedInventor: Alec G. Dodd
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Patent number: 4441859Abstract: A rotor blade for a gas turbine engine is provided with an internal tip damper comprising a damper weight which rotates under centrifugal load to cam itself into engagement between two components of the aerofoil, in particular the interior surface of the hollow aerofoil and the tip of a cooling air entry tube. By altering the degree of offset between the center of gravity of the weight and its support the frictional engagement may be varied.Type: GrantFiled: January 20, 1982Date of Patent: April 10, 1984Assignee: Rolls-Royce LimitedInventor: John H. R. Sadler
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Patent number: 4437810Abstract: A cooled vane for a gas turbine engine has a hollow aerofoil with apertures at its trailing edge for cooling air ejection. In order to control the flow of cooling air out of these apertures a metering insert extends between the opposed internal faces of the aerofoil adjacent the trailing edge and accurately defines the required flow areas.In a preferred embodiment the insert is of `hairpin` cross section and defines the flow area as channels between projections from the limbs of the `hairpin` which abut with the internal faces of the aerofoil. A cooling air entry tube then engages with the concavity of the hairpin, and the flow down the two flanks of the tube may be controlled by the flow area provided by the projections on the respective limb.Type: GrantFiled: February 24, 1982Date of Patent: March 20, 1984Assignee: Rolls-Royce LimitedInventor: Eric W. J. Pearce
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Patent number: 4413949Abstract: A turbine blade for a gas turbine engine has a hollow aerofoil and a root. A first insert for the distribution of cooling air in the aerofoil is inserted thereinto through an opening in the root but due to the relatively high camber of the blade the insert is such that it has to be displaced laterally after insertion. A second insert, also inserted through the opening, is provided to secure the first insert in position and to guide the cooling air from the opening to the first insert.Type: GrantFiled: September 30, 1975Date of Patent: November 8, 1983Assignee: Rolls Royce (1971) LimitedInventor: Alexander Scott
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Patent number: 4403917Abstract: A turbine nozzle vane of the kind which includes at least one inner hollow portion inside which a corrugated sleeve positioned against the sides thereof against protruding components. The protruding components against which the sleeve stands are arranged along the inner side and the outer surface according to a zone that stretches throughout most of the height and the width of which, being optimal at the base, changes gradually along the entire height before becoming minimal at the upper portion.Type: GrantFiled: January 5, 1981Date of Patent: September 13, 1983Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."Inventors: Denis R. G. Laffitte, Guy H. Louis, Alain M. M. Raybaud
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Patent number: 4396349Abstract: A turbine blade, more particularly a turbine nozzle vane, for a gas turbine engine, consisting of a structural metallic core enveloped at a distance by a ceramic blade jacket. Through provision a primarily highly heat-resistant, ceramic metal compound structure of the blade, the blade jacket is compressively prestressed spanwise between the blade shrouds in the inoperative condition of the turbine and where said compressive prestressing of the blade jacket, produced during assembly and which exists in the inoperative condition, is at least maintained during the operation condition by selecting for the metallic core of the blade, a material of average coefficient of thermal expansion and for the metallic inner and outer shrouds of the blade, and for the inner and outer metallic, sleeve-like components producing the axial prestress, materials of higher coefficients of thermal expansion, and for the highly thermally stressed ceramic blade jacket, a material of average coefficient of thermal expansion.Type: GrantFiled: March 12, 1982Date of Patent: August 2, 1983Assignee: Motoren-Und Turbinen-Union Munchen GmbHInventor: Alfred Hueber
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Patent number: 4381173Abstract: A coolable rotor blade assembly 10 of the type adapted for use in an axial flow gas turbine engine is disclosed. The assembly includes a rotor blade 12 and an impingement tube 14. A fiber metal seal 56 is disposed between the base of the rotor blade and the impingement tube. The seal contacts a seat 52 on the rotor blade and a face 54 on the impingement tube. The fiber metal seal has sufficient durability, flexibility, compressibility and density to enable sealing between the rotor blade and the impingement tube in a high temperature environment.Type: GrantFiled: August 25, 1980Date of Patent: April 26, 1983Assignee: United Technologies CorporationInventor: Melvin Freling
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Patent number: 4321010Abstract: A blade or vane structure for a gas turbine engine comprises a hollow aerofoil member and a cooling air entry tube within the hollow aerofoil member, the aerofoil member and the tube comprising a unitary cast structure. To make this structure it is proposed that a lost wax casting process should be utilized, with the internal cavities formed using ceramic cores formed with the aid of temporary, disposable pieces which define the space eventually occupied by the tube.Type: GrantFiled: July 31, 1979Date of Patent: March 23, 1982Assignee: Rolls-Royce LimitedInventors: Wilfred H. Wilkinson, Edwin Pateman, Anthony G. Gale, John Slinger
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Patent number: 4273075Abstract: A heat generating device includes a sealed metal drum with spaced peripheral fins and houses a cage-like agitator mounted on a rotatable shaft axially disposed therein and extending through one end for connection to a source of power. The agitator includes a plurality of elongated flat bar-like vanes arranged in close concentric relationship to the drum and supported by spaced apertured hubs on the shaft. The periphery of each hub has serrated type notches so that the vanes are tangential to the hubs and in off-set alignment with each other. Relative to the direction of rotation of the agitator, the leading edge of each vane is spaced inwardly from the trailing edge of the adjacent vane a predetermined distance to provide a restricted passageway.Type: GrantFiled: September 7, 1979Date of Patent: June 16, 1981Inventor: Dean A. Freihage
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Patent number: 4260336Abstract: The disclosed invention relates to coolant flow control apparatus for rotating heat exchangers such as used with a liquid cooled turbine blade and disc. By employing a combination of inlet and outlet orifices in the constrained coolant path of the apparatus, the liquid coolant can be made to rapidly reach and maintain supercritical temperature and pressure in the heat exchanger over a range of coolant heat absorption rates.Type: GrantFiled: December 21, 1978Date of Patent: April 7, 1981Assignee: United Technologies CorporationInventor: Bruce V. Johnson
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Patent number: 4257734Abstract: A vane for a gas turbine engine comprising a hollow body externally of aerofoil form. The inner surface of the body is provided with confronting grooves, extending in a direction along the length of the aerofoil form, at a location intermediate the leading and trailing edges of the aerofoil form for receiving two inserts. The first insert comprises two perforated panels situated inside a trailing region of the aerofoil form and defining therewith one or more air passages between the insert and the wall of the body. The first insert has portions which engage in the grooves in the wall of the body, and is provided with confronting grooves extending in a direction along the length of the aerofoil form at a location intermediate the leading and trailing edges of the aerofoil form. The second insert comprises a first panel extending across the void in the body, and has edges which engage in the confronting grooves in the first insert.Type: GrantFiled: March 5, 1979Date of Patent: March 24, 1981Assignee: Rolls-Royce LimitedInventors: Kenneth R. Guy, Terence W. Broom, Peter J. Maggs
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Patent number: 4252501Abstract: A hollow cooled vane for a gas turbine engine comprises at least two apertured members each mounted spaced from a separate part of the vane interior surface. The first of these members is provided with a supply of cooling air which passes through the apertures in the form of jets to impingement cool the respective first surface, and an interconnecting passage is provided to take this air to the second apertured member where it impingement cools the respective second surface.Type: GrantFiled: November 14, 1974Date of Patent: February 24, 1981Assignee: Rolls-Royce LimitedInventor: Peter G. Peill
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Patent number: 4190398Abstract: The turbine blades of a gas turbine engine are individually cooled through the internal circulation of a fluid coolant by the thermosiphon principle. Each turbine blade has associated therewith a closed-loop coolant passageway which is rotatable with the turbine rotor disk and which, in one embodiment, passes through a heat exchanger borne by, and rotatable with, a rotatable lubrication duct. The blade internal coolant is placed in heat exchange relationship with engine lubrication oil within the heat exchanger. The heated lubrication oil is then placed in heat exchange relationship with the engine fuel and the fuel thus heated is burned in the combustor, thereby returning at least a portion of the heat removed from the turbine blades to the engine power cycle. The cooling system is designed for simplified blade removal and replacement and the entire turbine can be removed from the engine as a sealed unit.Type: GrantFiled: June 3, 1977Date of Patent: February 26, 1980Assignee: General Electric CompanyInventors: Robert J. Corsmeier, James P. Rauf
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Patent number: 4183716Abstract: A hollow, air-cooled turbine blade of the type having a plurality of ridges and projections extended inwardly from an interior surface of said blade, an insert snugly fitted into a space defined and supported by the ridges and projections and cooling air passages for communicating the space inside the insert with an exterior blade surface, said air passage including a first passage for communicating the space through a space defined between the insert and a wall of the blade with the exterior blade surface and a second air passage for communicating the space within the insert through at least some of the projections directly with the exterior blade surface.Type: GrantFiled: January 4, 1978Date of Patent: January 15, 1980Assignee: The Director of National Aerospace Laboratory of Science and Technology Agency, Toshio KawasakiInventors: Kitao Takahara, Hiroyuki Nose, Makoto Sasaki, Kimio Sakata
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Patent number: 4177010Abstract: A cooled rotorblade has two separate cooling passages or series of passages in its aerofoil. One passage or series communicates with an aperture in the root or shank of the blade for the supply of cooling fluid while the other communicates with a hollow bush mounted in the shank to provide an inlet for cooling fluid. In addition to providing a cooling fluid inlet the bush serves to blank off an interconnection between the otherwise separate passages, the interconnection assisting the manufacturing process.Type: GrantFiled: March 22, 1978Date of Patent: December 4, 1979Assignee: Rolls-Royce LimitedInventors: Terence M. Greaves, Robert D. Summers
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Patent number: 4171184Abstract: A gas turbine rotor blade has a root portion and a hollow aerofoil supported from the root. Within the hollow aerofoil is mounted an air entry tube which has a closed end at or adjacent the tip of the aerofoil, the tube being sealed to the hollow blade interior at or adjacent the closed end so as to close off the otherwise open tip of the hollow aerofoil.Type: GrantFiled: April 18, 1978Date of Patent: October 16, 1979Assignee: Rolls-Royce LimitedInventors: Barry W. Lings, Anthony G. Gale
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Patent number: 4162136Abstract: A cooled blade for a gas turbine engine comprises an aerofoil portion having a longitudinally extending hollow. An air entry tube is mounted within the hollow and is pressed against a locating surface within the hollow by a resilient member such as a spring tube.Type: GrantFiled: April 1, 1975Date of Patent: July 24, 1979Assignee: Rolls-Royce LimitedInventor: Roger J. Parkes
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Patent number: 4142831Abstract: Individual coolant passages in the airfoil portion of a liquid-cooled turbine bucket are each provided with a plurality of inwardly protruding circumferentially-extending crimps or rings located at spaced intervals along each passage, each crimp, protrusion or ring extending along the inner periphery in a plane generally perpendicular to the wall of the coolant passage at that location. The main flow of liquid coolant moving in each such individual passage during turbine operation under the combined influence of centrifugal and Coriolis forces is broken up and dispersed over an enlarged area of the interior of the coolant passage upon encountering the protrusions.Type: GrantFiled: June 15, 1977Date of Patent: March 6, 1979Assignee: General Electric CompanyInventors: James T. Dakin, Kenneth A. Darrow, Myron C. Muth
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Patent number: 4105364Abstract: A vane for directing hot gases of a gas turbine engine and comprising at least one platform and a hollow aerofoil portion having an air entry tube extending spanwise therein, the tube being provided with a plurality of apertures, the size and the spacing therebetween being chosen to cause cooling fluid to impinge on the interior surface of the aerofoil portion in the form of a plurality of jets. A plurality of columnar projections extend between the interior surface of the aerofoil portion and the exterior of the air entry tube, each projection being positioned directly upstream of one of the apertures in the air entry tube with respect to the general flow of impinged fluid in the space between the interior surface of the aerofoil portion and the exterior of the air entry tube.Type: GrantFiled: December 7, 1976Date of Patent: August 8, 1978Assignee: Rolls-Royce LimitedInventor: Alec George Dodd
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Patent number: 4019831Abstract: The hollow interior of the blade is lined with a hollow insert and ribs to define a plurality of flow passages of narrow cross-section which connect a cooling-air chamber in the blade root with a cooling-air chamber in the blade tip. The chamber in the blade tip communicates with the interior of the insert and orifices are formed in the insert to exhaust air via a perforated partition through the trailing edge of the blade. The hollow insert is anchored in the blade root in various manners.Type: GrantFiled: August 28, 1975Date of Patent: April 26, 1977Assignee: Brown Boveri Sulzer Turbomachinery Ltd.Inventors: Clifford John Franklin, Hans Melliger
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Patent number: 3994622Abstract: A rotor blade capable of use in the high temperature environment of the turbine section of a gas turbine engine is disclosed. Various construction details which tend to equalize the metal temperature of the blade during operation also improve the cooling effectiveness of the cooling medium utilized. The system is built around convective, impingement, and film cooling techniques which are employed singly or in combination to improve the service life of the blade.Type: GrantFiled: November 24, 1975Date of Patent: November 30, 1976Assignee: United Technologies CorporationInventors: Paul Edwin Schultz, Gilbert Bardsley Wilcox