Patents Assigned to Roll-Royce Deutschland Ltd & Co KG
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Publication number: 20130306401Abstract: A method for manufacturing a sound absorber, the outer wall of which is provided with a plurality of recesses, with funnel-like cone elements each being assigned to the recesses inside the sound absorber, said cone elements having a larger opening facing radially outwards and a smaller opening facing radially inwards, with adjacent cone elements each being provided on a strip-shaped first carrier band, with cup elements being provided radially on the inside relative to the cone elements, and each cup element receiving one cone element, with adjacent cup elements each being provided on a strip-shaped first carrier band, with the first carrier bands being arranged adjacently in a first direction, and the second carrier bands being arranged adjacently in a second direction, with the directions crossing each other and the carrier bands being joined to one another and to the outer wall to form a rigid body.Type: ApplicationFiled: January 19, 2012Publication date: November 21, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & Co KGInventor: Predrag Todorovic
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Publication number: 20130306402Abstract: The present invention relates to a method for manufacturing a body provided with a honeycomb structure, which body is designed preferably axis-symmetrical, with sheet-metal parts being provided with a wave-like structuring by means of a forming process and formed to ring elements, with the sheet-metal parts being shaped and designed in a substantially identical way as regards their structuring, with adjacent sheet-metal parts being arranged offset to one another and then joined together to form the honeycomb structure.Type: ApplicationFiled: January 19, 2012Publication date: November 21, 2013Applicant: Rolls-Royce Deutschland Ltd & Co KGInventor: Predrag Todorovic
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Publication number: 20130302143Abstract: The present invention relates to a cooling device for a jet engine having an axial compressor with several compressor stages including a rotor with rotor blades, a stator with stator vanes and an annulus. In order to reduce the temperature of the components at the outlet of the high-pressure compressor by simple measures and hence to increase the efficiency of a jet engine, a slot-like branch opening surrounding the rotor for a cooling airflow diverted from the main airflow into a first cavity upstream of the rotor is provided upstream of the last compressor stage of the axial compressor, with passage openings being arranged in the rotor for passing on the diverted cooling airflow from the first cavity into a second cavity downstream of the rotor.Type: ApplicationFiled: December 14, 2011Publication date: November 14, 2013Applicant: Rolls-Royce Deutschland Ltd & Co KGInventor: Sacha Pichel
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Patent number: 8561940Abstract: An arrangement (1) for suspending a jet engine (12) to a supporting structure (5) attached to an aircraft fuselage, includes a suspension beam (6) to which the engine casing (13) is fitted by a forward suspension (7), a rearward suspension (8) and at least one thrust rod (9) arranged at an angle relative to the suspension beam (6). In order to provide an arrangement for the suspension of a jet engine (12) which enables weight to be saved and deformation of the jet engine (12) to be reduced, the rearward suspension (8) and the thrust rod (9) are connected to the engine casing (13) by a lightweight framework (11).Type: GrantFiled: December 10, 2010Date of Patent: October 22, 2013Assignee: Rolls-Royce Deutschland Ltd & Co KGInventors: Stephan Lisiewicz, Predrag Todorovic
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Publication number: 20130266469Abstract: For near net shape manufacturing of a high-temperature resistant component of complex design a high melting-point part of an intermetallic phase provided as a metal powder is mixed with a binder, and from the feedstock such formed a green compact substantially matching the final contour is produced by metal injection moulding, into the pores of said compact that remain after removal of the binder the low melting-point part of the intermetallic phase is infiltrated. The brown compact thereby created is mechanically processed, if required, and subjected to a specific heat treatment depending on the metallic phases used in order to create the intermetallic phase. This permits engine components consisting of intermetallic phases and having a geometrically complex structure to be manufactured cost-efficiently.Type: ApplicationFiled: November 18, 2011Publication date: October 10, 2013Applicant: Rolls Royce Deutschland Ltd & Co KGInventors: Dan Roth-Fagaraseanu, Alexander Schult
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Publication number: 20130266470Abstract: For near net shape manufacturing of high-temperature resistant engine components of geometrically complex design consisting of an intermetallic phase, a low melting-point metallic phase in the molten state or in a temperature range near the molten state is mixed with a high melting-point metallic phase provided as a metal powder, and the mixture is mechanically treated under the effect of kneading and shear forces, thereby heating it up and reducing its viscosity. In a subsequent injection moulding process the engine component substantially matching the final contour is formed and mechanically finish-machined, if required, and afterwards subjected to a heat treatment for creating an intermetallic phase.Type: ApplicationFiled: November 18, 2011Publication date: October 10, 2013Applicant: ROLLS ROYCE DEUTSCHLAND LTD & CO KGInventors: Dan Roth-Fagaraseanu, Alexander Schult
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Publication number: 20130266424Abstract: The present invention relates to a stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least two radial planes, as well as at least two stator vane adjusting rings connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device, characterized in that the actuating device is connected to the stator vane adjusting rings by means of a first transmission device and that a second transmission device, which is not coupled to the actuating device, is arranged essentially opposite to the first transmission device, with the second transmission device being connected to the stator vane adjusting rings.Type: ApplicationFiled: March 15, 2013Publication date: October 10, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Dirk SOEHNER
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Publication number: 20130259732Abstract: The present invention relates to a method for manufacturing thermally stressed engine components having a geometrically complex structure by metal injection moulding of metal powder mixed with a binder, by which method individual parts of the engine component are produced as separately moulded green compact sections and then as debindered brown compact sections which are joined together to form a two-part or multi-part brown compact and sintered in the assembled state, with the brown compact sections having differing shrinkage properties in the sintering process, depending on the type and size of the metal powder used, with at least one more heavily shrinking first brown compact section being automatically pressed against at least one second brown compact section during sintering of the assembled brown compact.Type: ApplicationFiled: November 25, 2011Publication date: October 3, 2013Applicant: Rolls-Royce Deutschland Ltd. & Co KGInventors: Alexander Schult, Dan Roth-Fagaraseanu
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Patent number: 8540492Abstract: The intake cone for a gas-turbine engine is wound in one piece from fiber compound material with fiber layers crossing one another. It is provided with a fiber compound belt, wound in the circumferential direction of the intake cone, in the connecting area with a mounting flange, which is of segmented design and thus features reduced circumferential stiffness, of a metallic retaining ring attached to a fan rotor disk. The intake cone is easily manufacturable with almost constant wall thickness and in high quality, can reliably be subjected to non-destructive testing and, in combination with the mounting flange, which is flexible in the radial direction, ensures safe connection of the two components despite the different thermal and elastic behavior of the respective materials.Type: GrantFiled: March 25, 2010Date of Patent: September 24, 2013Assignee: Rolls-Royce Deutschland Ltd & Co KGInventor: Karl Schreiber
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Patent number: 8534997Abstract: A main flow path of a fluid flow machine includes N adjacent member blade rows firmly arranged relative to each other in both a meridional direction m and a circumferential direction u. A number of the member blade rows, N, is greater than/equal to 2 and (i) designates a running index with values between 1 and N. A trailing edge HK (i) of a blade of the member blade row (i) is spaced from a leading edge VK(i+1) of a blade of the adjacent, downstream member blade row (i+1) by a meridional edge distance D in a meridional plane established by axial direction x and radial direction r. A value of D along a height of the main flow path increases towards the main flow path confinement at least along a part of the area between the main flow path center and the main flow path confinement.Type: GrantFiled: April 30, 2010Date of Patent: September 17, 2013Assignee: Rolls-Royce Deutschland Ltd & Co KGInventor: Volker Guemmer
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Patent number: 8529361Abstract: A drive shaft, in particular a radial shaft for a gas-turbine engine, includes a metallic and hollow shaft shank 1 with load transfer elements 2, 10, 11 integrally formed onto its ends. The shaft shank 1 includes a metal tube 3, 9 prefabricated as a semi-finished part, designed only for transmission of torsional loads and having a constant wall thickness. An outer or inner reinforcement 5, 8 intended only for ensuring the necessary bending stiffness is provided on the outer and/or inner circumferential surface of the metal tube 3, 9 and made from a fiber-composite layer 13, 13? with fibers oriented in the longitudinal direction of the drive shaft. The inner fiber-composite layer 13 acting as outer reinforcement 5 is sheathed with an outer fiber-composite layer 14 made from fibers oriented at an angle of 60° to 90° relative to the longitudinal direction.Type: GrantFiled: October 10, 2011Date of Patent: September 10, 2013Assignee: Rolls-Royce Deutschland Ltd & Co KGInventors: Gerald Hechler-Stabbert, Alexander Pabst
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Publication number: 20130230383Abstract: The present invention relates to an aircraft gas turbine having a fan rotatable about an engine axis in the inflow region of the aircraft gas turbine, with the fan having several fan blades, with each fan blade being moveably mounted on a hub rotatable about the engine axis by means of its blade root on an area which is at the front in the flow direction, and with each fan blade being moveably mounted on an area at the rear in the flow direction, on an adjusting disk axially displaceable relative to the engine axis and non-rotatable with the hub, with the pitch angle of the fan blades being variable by the axial movement of the adjusting disk.Type: ApplicationFiled: January 11, 2013Publication date: September 5, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Predrag TODOROVIC
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Publication number: 20130219982Abstract: The present invention describes a rolling tool device for compression rolling of, in particular, blade elements of a rotor area of a jet engine provided with a tool carrier. The tool carrier is connectable to a carrier spindle. Furthermore, two pliers-type bodies are rotatably connected to the tool carrier. The pliers-type bodies are each provided with a rolling area, with a distance between the rolling areas being variable in dependence of the rotary movement of the pliers-type bodies. In accordance with the present invention, an axis of the carrier spindle in the state connected to the tool carrier passes between the rolling areas through a contact point present at a distance between the rolling areas equal to zero.Type: ApplicationFiled: April 12, 2012Publication date: August 29, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventors: Goetz G. Feldmann, Karsten Roettger, Stefan Zenk
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Patent number: 8518223Abstract: When forming metallic components, in particular three-dimensionally curved blades, which constitute a single piece with the blading of turbomachine rotor wheels, the linear oscillation of the electrode acting as a tool is superimposed by a circular oscillation, enabling the electrode to turn into the workpiece conformally with its shape. Further forming is performed by circular oscillation with circular feed in the one and/or the other direction. An embodiment of the corresponding apparatus comprises an electrode holder (9) with linear feed (Zvor) and linear oscillation (Zosz) and a workpiece holder (5) with circular oscillation (Cosz) and circular feed (Cvor).Type: GrantFiled: October 23, 2008Date of Patent: August 27, 2013Assignee: Rolls-Royce Deutschland Ltd & Co KGInventor: Rainer Mielke
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Publication number: 20130216391Abstract: The present invention describes a method for the production of a one-piece rotor area, preferably of a jet engine. The rotor area includes an annular base body and several, circumferentially distributed blade elements extending essentially radially from the base body. Residual stresses are imparted to the blade elements in surface-near areas by way of roller compression using a rolling tool introduced between the blade elements. During roller compression, one each area of a blade element is arranged between areas of the rolling tool, with longitudinal sides of the blade element being simultaneously roller-compressed. According to the present invention, the rolling tool is radially introduced between the blade elements and the surfaces of the blade elements are roller-compressed, thus at least the blade elements having a roller-compressed surface.Type: ApplicationFiled: April 12, 2012Publication date: August 22, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Goetz G. Feldmann
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Publication number: 20130205753Abstract: An aircraft gas turbine thrust-reversing device has an engine cowling, the rear area of which is displaceable in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular space to a front and stationary area of the engine cowling. The rear area of the engine cowling is coupled to deflecting elements and blocker doors, which in the forward thrust position are arranged completely inside the front area of the engine cowling. A drive element is provided between the front area and the rear area, which effects the axial displacement of the rear area. The drive element is a two-stage drive element, effecting in a first stage an axial displacement by an axial partial displacement path, and in a second stage an axial displacement by the full axial displacement path.Type: ApplicationFiled: February 4, 2013Publication date: August 15, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
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Publication number: 20130206676Abstract: The present invention relates to a measuring device having a pressure sensor, with the pressure sensor having a measuring cell designed to detect a pressure. It is provided that the measuring cell of the pressure sensor is arranged in or adjacent to a protective cell filled with a measuring fluid that can be coupled to a fluid to be measured via at least one separating membrane. It is furthermore provided that a damping device is arranged in the protective cell between the separating membrane and the measuring cell, said damping device including a restrictor and a downstream volume expansion means that provides an increased volume between the restrictor and the measuring cell in the event of a pressure increase in the measuring fluid.Type: ApplicationFiled: February 11, 2013Publication date: August 15, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Rolls-Royce Deutschland Ltd & Co KG
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Publication number: 20130205788Abstract: The present invention relates to a premix burner of a combustion chamber of a gas turbine with at least one annular duct for supplying air and fuel, including a radially outer and a radially inner combustion chamber wall relative to a burner central axis and with at least one swirler arranged in the duct, said swirler including several flow-guiding elements distributed around the circumference of the duct cross-section, characterized in that at least one radially inner duct wall is provided in the area of the flow-guiding elements with a concave recess of the annular groove type.Type: ApplicationFiled: February 5, 2013Publication date: August 15, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventor: Rolls-Royce Deutschland Ltd & Co KG
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Publication number: 20130199187Abstract: The present invention relates to an annular gas-turbine combustion chamber having a radially outer and a radially inner combustion chamber wall relative to a machine axis, a combustion chamber head and a combustion chamber outlet nozzle, where the combustion chamber head includes several fuel nozzles spread over its circumference for supplying air and fuel, the latter exiting in an outlet surface of the fuel nozzles, where the respective fuel nozzle has a burner axis which is vertical to the outlet surface and where the intersections of the burner axes with the outlet surfaces define a circular burner centerline around the engine axis, characterized in that a cross-sectional area of the fuel nozzle radially outside the burner centerline is identical to a cross-sectional area radially inside the burner centerline.Type: ApplicationFiled: January 31, 2013Publication date: August 8, 2013Applicant: Rolls-Royce Deutschland Ltd & Co KGInventor: Rolls-Royce Deutschland Ltd & Co KG
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Publication number: 20130202088Abstract: The present invention relates to a method for radiographically inspecting a component by means of X-rays, where at least one component surface to be radiographed is provided with a surface structure, with at least the surface provided with the surface structure being smoothed by means of a smoothing material to level out the surface structure, with at least one organic compound and at least one metal powder being used as smoothing material, with the X-ray absorption behaviour of the smoothing material essentially equaling the X-ray absorption behaviour of the material of the component, as well as to a smoothing material for carrying out the method in accordance with claim.Type: ApplicationFiled: August 9, 2010Publication date: August 8, 2013Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KGInventors: Karl Schreiber, Josef Geitner
