Abstract: A device for adjusting the power of a power pack driving a helicopter rotor, including a device for dosing the fuel feed rate. An electronic control device is further provided that acquires an input signal corresponding to the rotational speed of the rotor. A processor processes the input signal by using a differentiating element and a summing element. Further, a threshold comparator receives the output signal of the processor and an actuating device receives the output signal of the electronic control device and actuates the device for dosing the fuel feed rate.
Type:
Grant
Filed:
October 15, 2002
Date of Patent:
May 4, 2004
Assignee:
Turbomeca
Inventors:
Christian P. Noussitou, Jean-Philippe J. Marin
Abstract: A multi-duct diffusion exhaust device for a turbomachine. The exhaust device including an annular inlet, an outer casing shaped symmetrically overall with respect to an axis, one or more internal partitions defining several roughly concentric ducts for an exhaust stream to flow through, and an absorbent coating capable of absorbing some of the acoustic energy generated by the flow. The absorbent coating being provided on at least one of a surface of one internal partition and an interior surface of the outer casing. The absorbent coating having a thickness that is tailored along a length of the exhaust device to optimize the flow in the ducts by maintaining progressive diffusion and avoiding detachment near stationary surfaces.
Abstract: A turbomachine includes blade stages on the trajectory of a flow of air or gas delimited by a symmetrical wall along the axis of the turbomachine. The wall has orifices communicating with a cavity outside the flow of air of generally symmetrical structure. The cavity is connected to a pipe. Symmetry degrading arrangements are provided inside the cavity, for example in the form of a portion of tube mounted in the pipe to project partly into the cavity.
Abstract: A turbomachine includes blade stages on the trajectory of a flow of air or gas delimited by a symmetrical wall along the axis of the turbomachine. The wall has orifices communicating with a cavity outside the flow of air of generally symmetrical structure. The cavity is connected to a pipe. Symmetry degrading arrangements are provided inside the cavity, for example in the form of a portion of tube mounted in the pipe to project partly into the cavity.
Abstract: The present invention relates to a gas-turbine combustion chamber comprising at least a zone (11) referred to as pilot combustion zone into which at least a first pilot fuel injection means (3) and an associated first oxidizer injection means (4) open; a main combustion zone (12) into which at least a second main fuel injection means (7) and an associated second oxidizer injection means (8) open, all of it being maintained under a pressure P1 inside an enclosure (14). According to the invention, said chamber further comprises a mechanical means (15-19) for controlling the second flow of oxidizer, which reacts to the pressure difference between the inside (P1) and the atmospheric pressure (Po) outside enclosure (14), said pressure difference being directly linked with the engine speed.
Type:
Grant
Filed:
June 11, 1999
Date of Patent:
July 24, 2001
Assignees:
Institut Francais du Petrole, Turbomeca
Inventors:
Guy Grienche, Gérard Schott, Jean-Hervé Le Gal, Gérard Martin, Patrice Laborde, Raphaël Spagna
Abstract: The process for making a forged nickel-base superalloy part for use in the 700-900.degree. C. range which includes the steps of:a) providing a nickel-base superalloy having the following composition:______________________________________ percentage by weight ______________________________________ Cr 15.5-18 Co 14.0-15.5 Mo 2.75-3.25 W 1.00-1.50 Ti 4.75-5.25 Al 2.25-2.75 Zr 0.025-0.050 B 0.01-0.02 C 0.006-0.025 Cu .ltoreq.0.10 Mn .ltoreq.0.15 Fe .ltoreq.0.50 Si .ltoreq.0.2 P .ltoreq.0.05 S .ltoreq.0.05 Ni balance ______________________________________and eventual impurities, where the weight ration B/C is equal to or greater than 1.1;b) forging said nickel-base superalloy to obtain an as-forged part;c) submitting the as-forged part of step b) to a solution heat treatment at a temperature ranging from 10 to 30.degree. C. above the .gamma.' phase solvus temperature;d) quenching the solution heat treated forged part resulting from step c) at a quenching rate above 100.degree. C.
Abstract: A multiple layer erosion resistant coating on a substrate comprises alternate layers of tungsten and titanium diboride. All of the layers have the same thickness and preferably have thickness's of between 0.3 and 1 micrometer to give improved erosion resistance. The layers are produced by spattering.
Abstract: A multiple layer erosion resistant coating on a substrate comprises alternate layers of tungsten and titanium diboride. All of the layers have the same thickness and preferably have thickness's of between 0.3 and 1 micrometer to give improved erosion resistance. The layers are produced by sputtering.
Abstract: The present invention relates to a multilayer material useful as an anti-erosion and anti-abrasion coating, and to a process for producing the multilayer material at low temperatures. The multilayer material comprises a substrate covered with at least one metallic tungsten ductile layer and at least one hard layer of a solid solution of an additional element chosen from carbon or nitrogen or a mixture of carbon and nitrogen in tungsten or a tungsten alloy, the two types of layers ar alternating. The multilayer material is particularly useful as a coating for parts used in aeronautics.
Type:
Grant
Filed:
April 26, 1996
Date of Patent:
December 30, 1997
Assignees:
Commissariat a l'Energie Atomique, Turbomeca, L'Etat Francais represente par le Delegue general pour l'Armement
Inventors:
Serge Paidassi, Jacques Ernoult, Michel Brun, Pierre Monge-Cadet, Yves Pauleau, Guy Farges
Abstract: A multiple layer erosion resistant coating on a substrate comprises alternate layers of tungsten and titanium diboride. All of the layers have the same thickness and preferably have thickness's of between 0.3 and 1 micrometer to give improved erosion resistance. The layers are produced by sputtering.
Type:
Grant
Filed:
March 22, 1995
Date of Patent:
August 12, 1997
Assignees:
Rolls-Royce plc, Turbomeca Societe Dite, Etat Francais-Delegation Generale Pour L'Armement
Inventors:
David S. Rickerby, Pierre Monge-Cadet, Guy Farges
Abstract: The invention provides a regulating system (23) for controlling the heating of the gases on the downstream side of the regulating system, attenuating the aerodynamic noise produced by the gyratory flow on the downstream side of the directing vanes (24) of the regulating system and facilitating the endoscopic inspection of the blades and vanes of a compressor (3) owing to the provision of a throughway passage (27) in the regulating system (23), and in particular a throughway opening in at least one directing vane (24).
Type:
Grant
Filed:
January 30, 1995
Date of Patent:
January 16, 1996
Assignee:
Turbomeca
Inventors:
Pierre Biscay, Alain J. Farrando, Philippe D. Joubert, Jean-Bernard Martin, Hubert H. Vignau
Abstract: A device for connecting in rotation two substantially coaxial elements (10,12), of the type comprising a splined shaft (10,20), a splined hub (24) and clamping elements for achieving a relative axial immobilization between the splined shaft and splined hub. A first end portion of the splined shaft (20) is provided with a centering ring (30) having an outer surface (34) including an outer screw threading (36) having unsymmetrical flanks, which ring (30) is screw-threadedly mounted in a corresponding portion (42) of the splined hub (24) comprising a complementary tapping (44) having unsymmetrical flanks. The second end portion (46) of the splined shaft (20) comprises an outer screw threading (48) on which is screw-threadedly mounted an axial clamping nut (50) having a radial face (52) cooperating with a confronting radial face (54) on the splined hub (24). The invention is of utility in connecting in rotation a power shaft and a rotating element of a turbomachine.
Abstract: Turbomachine wheel having blades mounted on a rotor including an annular peripheral ring in which are formed open axial recesses each of which receives the root of a blade. Each blade is radially retained in the recess by cooperation of complementary shapes of the fir tree type, with a direction of fitting being parallel to the axis of the rotor. The blade root is axially immobilized in the recess by a first flange and a second flange which are respectively disposed adjacent to the opposite lateral faces of the rotor, and at least partly close the opposite axial ends of the recesses for the roots of the blades. The first flange is fastened to the rotor by a bayonet type device whose lugs are formed on the first flange and are received in notches formed in the annular ring of the rotor with open ends of the notches for engagement of the lugs opening onto the transverse walls which define the recesses.
Abstract: An object (12) is irradiated by means of a divergent and polychromatic beam of X-rays for producing a diagram composed of Kikuchi pseudo-lines. An X-ray generator (4) is mounted on a stand (1), and an automatic handler (13) presents the objects (12) in confronting relation to the microfocus (F) of the generator. An intensity amplifier (6) and a video camera (7) record the obtained diagrams composed of the pseudo-lines. The handler apparatus is controlled by an electronic device (17).
Abstract: According to this method the linear expansion (.DELTA.L) of a reference shaft is measured with reference to that of the power shaft. The linear expansion of the reference shaft (R.sub.3) is converted into a movement of rotation of an annular phonic wheel (B.sub.3) by means of the free end (J) of this shaft engaged in a helical groove in the inner surface of the annular wheel (B.sub.3).
Type:
Grant
Filed:
August 26, 1986
Date of Patent:
October 4, 1988
Assignee:
Turbomeca
Inventors:
Roger H. L. Barbe, Alain M. Dufau, Edgar H. Haehner