Abstract: Distributor sectors (25) on which fixed vanes are placed adjacent to a casing (31) by means of sealing sectors (32) alternating with them in the axial direction and provided with force resistant faces (37; 39) through which forces exerted on the distributor sectors are transmitted to the casing. The inner surface of the casing (31) is smoother and is not fitted with any hooks; consequently, this casing (31) is less complicated to make and is less mechanically stressed to retain the distributor sectors, and the distributor sectors may be installed by a purely axial movement.
Type:
Application
Filed:
October 5, 2004
Publication date:
February 24, 2005
Applicant:
SNECMA MOTEURS
Inventors:
Patrick Girard, Sebastien Imbourg, Philippe Pabion, Jean-Luc Soupizon
Abstract: The invention relates to a device for holding an annular end plate (5) against a radial face (4) of a rotor disc (1), the said disc having in the said radial face an annular recess (7) behind a collar (13) extending radially outwards, and the said end plate (5) having, in its radially inner part, an annular base bearing against the radially outer wall of the recess (7) and a foot extending radially inwards in the recess (7) from the base, the said device comprising a split annular retaining ring disposed in the recess (7).
Abstract: The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several passages (34,36,72) enabling initiation of a cooling air film (D2) along the hot inner surface (30) of the outer axial wall and initiation of a cooling air film (D1) along the hot inner surface (32) of the inner axial wall, the outer axial wall and the inner axial wall being multi-perforated roughly over their full length in order to enable reinforcement of the cooling air films. According to the invention, the outer axial wall and the inner axial wall are provided, in an upstream part, with a first zone (54,40) of perforations (38) formed such that cooling air is introduced inside the combustion chamber in reverse flow.
Abstract: The invention relates to a device for determining a measurement of mass flow of fluid for a combustion chamber comprising a fluid metering device and a means of measuring the position of the metering device being measured.
Abstract: A device for guiding pivoting of variable-pitch vanes in a turbomachine, each vane having a pivot formed by a cylindrical axial shank which is guided in a cylindrical chimney of the casing and in a cylindrical orifice of a stationary element which surrounds the outside of the casing and which is centered and fixed relative thereto. The invention improves pivotal guidance of variable-pitch vanes.
Type:
Application
Filed:
July 8, 2004
Publication date:
February 24, 2005
Applicant:
SNECMA MOTEURS
Inventors:
Pierre Debeneix, Arnaud Langlois, Erick Boston, Frederic Leman, Vincent Garnier, Jacques Audet
Abstract: The invention relates to an axial compressor disk for a turbomachine, the disk including a bleed system for bleeding air centripetally from the compressor stream in order to cool a turbine, said bleed system comprising channels formed outside the working section of the disk and parallel to said section in an extra thickness projecting away from said working section on a face of said disk, wherein the bleed channels are axially open over substantially their entire radial extent.
Type:
Grant
Filed:
January 16, 2003
Date of Patent:
February 22, 2005
Assignee:
Snecma Moteurs
Inventors:
Philippe Avignon, Antoine Robert Alain Brunet, Patrick Claude Pasquis
Abstract: The system enables an increase in the guidance length of the outer pivot (11) of the vane (10), so that the bushing (50) can be extracted without needing to open the stator casing. It mainly includes a bushing (50) placed inside a bossing (21) of the stator, the length of which is greater than the length of the bossing (21) projecting outwards from the bossing. Thus, the contact length of the outer pivot (11) is prolonged. The bushing is terminated at its end by a gripping hook (41) to enable extraction of the bushing by means of a claw. It is advantageously also provided with a positioning edge (42).
Abstract: The invention provides a combustion chamber comprising a chamber wall disposed radially inside a casing, an igniter plug for igniting the air-fuel mixture, the plug being mounted on said casing and comprising a body with a free end that is disposed in an opening formed through said chamber wall with a large amount of clearance to accommodate relative displacement between said casing and said chamber wall, and a sealing device provided between said body and the perimeter of said opening, said sealing device comprising an annular plug-guide through which said body passes, the plug-guide being slidably mounted at the radially-outer end of an annular support whose base is secured to said perimeter, wherein the support is secured to the radially-outer portion of a chimney passing through said opening and presenting at its radially-inner end a collar bearing against the inside face of the chamber wall, and wherein a cooling circuit for said collar is provided.
Type:
Application
Filed:
June 18, 2004
Publication date:
February 10, 2005
Applicant:
SNECMA MOTEURS
Inventors:
Didier Hernandez, Mario De Sousa, Patrice Commaret
Abstract: The invention proposes a process for obtaining a flexible/adaptive thermal barrier, the thermal barrier comprising a ceramic layer (44) deposited on a substrate (40) covered with a sublayer (42), the ceramic layer (44) being deposited by thermal spraying using a torch (30). Such a process is noteworthy in that: a. the ceramic layer (44) is deposited in a single pass; and b. the torch (30) is set to give the ceramic layer (44) a thickness of at least 80 ?m.
Abstract: A gas turbine blade of a turbomachine includes in its central portion a centrally-located first cooling circuit at least a suction side cavity, at least a pressure side cavity, at least a central cavity extending between the suction side cavity and the pressure side cavity, a first air admission opening at a radially bottom end of the suction side cavity, a second air admission opening at a radially bottom end of the pressure side cavity, at least a first passage putting a radially top end of the suction side cavity into communication with a radially top end of the central cavity, at least a second passage putting a radially top end of the pressure side cavity into communication with the radially top end of the central cavity, and outlet orifices opening out both into the central cavity and into the pressure side face of the blade.
Abstract: The invention relates to a connection between a first piece (D1) ending in a first ring (12) provided with a succession of holes and notches, the axis of the first ring being centred on the axis of rotation of the compressor rotor in order to be attached to the intake of the compressor rotor, and an assembly formed by a second rotor piece (D2) fixed to a third rotor piece (D2). The second piece (D2) forms the intake of the compressor rotor and ends downstream in a second ring (32) comprising holes. The third piece ends upstream in a third ring (32) comprising holes, and the second and third rings are arranged against each other, so as to place their holes in alignment, and are fixed together by first fastening means.
Type:
Application
Filed:
July 7, 2004
Publication date:
February 3, 2005
Applicant:
SNECMA MOTEURS
Inventors:
Didier Escure, Gerard Miraucourt, Francis Soniak, Erick Boston, Jacques Audet, Marie-France Bourgeois, Daniel Dao
Abstract: In a variable-section turbomachine nozzle, a plurality of flexible follower flaps are provided that are interposed between adjacent controlled flaps against which the follower flaps are held by fastener means, each follower flap comprising a plurality of independent transverse boxes mounted side by side in a support sheet, the boxes contacting one another via their longitudinal edges and being held in the support sheet via their lateral edges which are engaged in the longitudinal edges of the support sheet, which longitudinal edges define respective bearing zones for bearing against the adjacent controlled flaps.
Abstract: The invention relates to a method of supplying cooling air to the hot portions of a turbojet that comprises, from upstream to downstream: a compressor; a diffuser; a combustion chamber; a distributor; and a turbine driving said compressor, in which method a flow of air is bled from the flow of air delivered by the compressor, the bled-off flow is cooled in a heat exchanger situated radially outside the combustion chamber, and is then directed radially inwards via the stationary blades of the distributor and used for cooling the moving wheel of the turbine, the method wherein the flow of cooling air is bled from the zone of the end of the combustion chamber that surrounds the diffuser, and wherein the stationary blades of the distributor are also cooled by a second flow of air bled from the diffuser.
Abstract: Prior to passing through pumping apparatus effluent gas containing hydrocarbons is subjected to washing by being sprayed with aromatic type oil in oil-recirculating washing apparatus. Polycyclic aromatic hydrocarbons contained in the effluent gas are trapped by being absorbed in the oil. The method is suitable for treating effluent gas coming from an installation for chemical vapor deposition or infiltration using a reagent gas containing a precursor for pyrolytic carbon, or else coming from a cementation installation.
Type:
Grant
Filed:
October 4, 2002
Date of Patent:
February 1, 2005
Assignee:
Snecma Propulsion Solide
Inventors:
Yvan Baudry, Jean-Pierre Lambert, Bernard Delperier, Jean-François Potin
Abstract: A device for fastening two parts to each other comprises fastening screws extending in aligned passages in the two parts, and means for preventing the screw heads from moving. The means for preventing the screw heads from moving comprise at least one removable element including means for preventing rotation relative to one of the two parts for fastening together.
Type:
Application
Filed:
June 22, 2004
Publication date:
January 27, 2005
Applicant:
SNECMA MOTEURS
Inventors:
Daniel Dao, Eric Landragin, Francois Garcin
Abstract: A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having means for producing exhaust gas and a gas exhaust nozzle for generating thrust for supersonic flight speeds, and at least one separate auxiliary propulsion assembly dissociated from said engine, having no gas generator, and capable of generating thrust for takeoff, landing, and subsonic flight speeds. The system further comprises gas flow tapping means movable between a position in which they tap off at least a fraction of the exhaust gas produced by said engine and feed it to said propulsion assembly to enable it to generate thrust for takeoff, landing, and subsonic cruising flight, and a position in which the gas produced by the engine is directed solely to the engine nozzle for supersonic cruising flight.
Type:
Grant
Filed:
June 13, 2002
Date of Patent:
January 25, 2005
Assignee:
SNECMA Moteurs
Inventors:
Michel Franchet, Yann Laugier, Jean Loisy
Abstract: A device for injecting cooling air into a turbomachine turbine rotor, the device comprising a plurality of injectors distributed regularly around a longitudinal axis of the turbomachine and mounted between an inner shroud and an outer shroud, each injector of aerodynamic profile comprising, between a leading edge and a trailing edge, a suction side wall and a pressure side wall, the cooling air passing through the injectors being ejected towards through orifices in the turbine rotor via a flow section forming an aerodynamic throat between the trailing edge of one injector and the suction side wall of an immediately adjacent injector, wherein, in order to modify the section of the aerodynamic throat as a function of the temperature of the cooling air passing through the injectors, each injector comprises a bimetallic structure with a first metal material forming a major portion of the structure of the injector and having a first coefficient of thermal expansion, and a second metal material forming a complement
Abstract: A guide device for guiding a variable-pitch blade, in particular in a turbomachine compressor, the blade having a pivot formed by a cylindrical axial shank (6) mounted in a cylindrical housing (10) of a casing and pivotally guided about an axis in said housing by bearings, the device being characterized in that said bearings are abutment bearings (14, 15) with conical rollers (17), the axes of the rollers being substantially perpendicular to the pivot axis of the blade.
Type:
Application
Filed:
May 5, 2004
Publication date:
January 13, 2005
Applicant:
SNECMA MOTEURS
Inventors:
Pierre Debeneix, Alain Bromann, Francois Buffenoir
Abstract: A gas turbine, in particular a high pressure turbine for an airplane engine, the turbine comprising moving blades (10) with tips that are fitted with radially slidable stubs (26) for being pressed in operation by centrifugal forces against the inside surface of the casing (16) of the turbine in order to eliminate radial clearance between said surface and the tips of the blades (10).