Patents Assigned to Rolls-Royce plc
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Publication number: 20090069454Abstract: Components formed with a polymer matrix are subject to problems in relation to shrinkage as that polymer matrix cures. With regard to components incorporating reinforcing fibres, such shrinkage may tension and curl the fibres resulting in stresses within the component and premature failure. By providing voids or expandable beads, which alter in size to compensate for volumetric variation in the polymer matrix during curing, such tension may be avoided. Advantageously, the voids or expandable beads have a shape such that there is a reduction in void surface area as the void or expandable bead increases in volume.Type: ApplicationFiled: August 28, 2008Publication date: March 12, 2009Applicant: ROLLS-ROYCE PLCInventor: Alison Jane McMillan
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Patent number: 7502128Abstract: There are difficulties with regard to observing a rotating component in an obscuring environment such as typical of a gas turbine engine where there may be soot, flames, light signals and moisture. It will be understood that simply increasing the light intensity will increase scatter and therefore may “blind” a camera in terms of viewing distinctive features and targets within a rotating component. The present arrangement provides a mirror with an aperture such that an illuminating light source is directed towards a rotating component such that reflection is similarly incident upon the reflective mirror and light deflected to the camera. In such circumstances the camera is less susceptible to light scatter obscuration.Type: GrantFiled: June 12, 2006Date of Patent: March 10, 2009Assignee: Rolls Royce, PLCInventor: Harold Heyworth
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Patent number: 7501079Abstract: An irreversible temperature indicating paint comprises 0.7 wt % to 0.9 wt % toluidine red, 7 wt % to 32 wt % cobalt aluminium spinel and glass, 7 wt % to 32 wt % cobalt chromite spinel, alumina, purple gold and frit, 37 wt % to 41 wt % acrylic resin, 20 wt % to 23 wt % silicone resin excluding solvent. The solvent comprises a mixture of 80% 1-methoxy-2-propanol and 20% dipropylene glycol monomethyl ether. A particular irreversible temperature indicating paint comprises 0.78 wt % toluidine red, 19.55 wt % cobalt aluminium spinel and glass, 19.55 wt % cobalt chromite spinel, alumina, purple gold and frit, 39.1 wt % acrylic resin, 21.1 wt % silicone resin excluding solvent. The irreversible temperature indicating paint is used to determine the temperatures to which various parts of turbine blades, turbine vanes or other components are subjected in operation of a gas turbine engine.Type: GrantFiled: June 6, 2005Date of Patent: March 10, 2009Assignee: Rolls-Royce plcInventor: Hugh M. L. Watson
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Patent number: 7500347Abstract: A variable geometry combustor having a combustor liner that defines at least one dilution port in order to provide air to a dilution zone within the combustor. At least one valve is positioned adjacent the dilution port for controlling the flow of air through the dilution port wherein the valve is settable to maintain one of a plurality of different open configurations.Type: GrantFiled: August 10, 2004Date of Patent: March 10, 2009Assignee: Rolls-Royce plcInventors: Noel A Sanders, Carl C Bourne, Anthony J Moran, Paul Fletcher, Philip P Walsh
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Patent number: 7500352Abstract: A gas turbine engine (2) comprises a fan unit (4,18,36,42,44,46) in flow relationship with an engine core and a bypass duct, of which said engine core and bypass duct (16) are in parallel flow relationship with each other. The engine core comprises a compressor (6), a combustor (8) and a turbine (10), with an inner casing (12) provided around said engine core which defines the engine core intake (32). The bypass duct (16) is defined by an outer casing (14) radially spaced apart from the fan unit (4,18,36,42,44,46) and the inner casing (12) along at least part of the length of the gas turbine engine (2). Bypass air compression means (28) are provided such that, under substantially all engine power conditions, air at exit from the bypass duct (16) is at a greater pressure than air delivered to the engine core intake (32).Type: GrantFiled: May 23, 2005Date of Patent: March 10, 2009Assignee: Rolls-Royce PLCInventor: Stephen J. Bradbrook
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Publication number: 20090060718Abstract: A component (10) and method for manufacturing a component. The component comprises first and second panels (16, 18) spaced apart from each other, the first panel (16) having at least one protrusion (20) extending therefrom towards the second panel (18). The protrusion (20) extends partially across the space (19) between the first and second panels so as to define a free end of the protrusion. The free end is surrounded by damping material (24).Type: ApplicationFiled: July 7, 2008Publication date: March 5, 2009Applicant: ROLLS-ROYCE PLCInventors: Keith C. Goldfinch, Oliver M. Strother, Julian MacKechnie-Jarvis
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Publication number: 20090060736Abstract: A compressor 13, for example for a gas turbine engine (10, FIG. 1), comprises a circumferentially extending static casing component 20 defining a generally axially extending main gas flow path 24. The compressor also includes a rotating aerofoil arrangement 26 comprising an aerofoil support 30 and a plurality of aerofoils 28 extending radially from the aerofoil support 30 into the main gas flow path 24. The aerofoil support 30 and the circumferentially extending static casing component 20 define a circumferentially extending generally radial passage 40 having an outlet 42 in communication with the main gas flow path 24 through which leakage air may flow into the main gas flow path 24, and the static casing component 20 includes a continuous circumferentially extending projection formation 44 projecting into the radial passage 40 to control the flow of leakage air into the main gas flow path 24.Type: ApplicationFiled: August 18, 2008Publication date: March 5, 2009Applicant: ROLLS-ROYCE PLCInventor: Giulio Zamboni
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Publication number: 20090057489Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels and the web by applying internal pressure between the panels so as to form a series of internal cavities partitioned by the web. The method further includes the step of either cutting the web (30) across its entire width or causing the web to fail across its entire width so as to define an aerofoil having first and second panels with at least one protrusion extending from the first panel partially across the space between the first and second panels.Type: ApplicationFiled: July 7, 2008Publication date: March 5, 2009Applicant: ROLLS-ROYCE PLCInventors: Keith C. Goldfinch, Oliver M. Strother, Julian Mackechnie-Jarvis
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Publication number: 20090060715Abstract: A component, such as a turbine blade of a gas turbine engine, has an internal cooling system which includes a passage (28) having a passage inlet (22) and a passage exit (30), which may be in the form of passageways at or adjacent to the trailing edge of the component. The passage (28) is divided into chambers (52, 54, 56, 58) by partitions (40, 42, 44) which extend from one wall (34) of the component and terminate short of the opposite wall (36) to provide gaps (46, 48, 50) to permit chord-wise cooling air flow from the passage inlet (22) to the passage exit (30). The gaps (46, 48, 50) force the cooling air to pass adjacent the hot walls (34, 36), so increasing the heat transfer coefficient between the cooling air and the material of the component.Type: ApplicationFiled: August 25, 2008Publication date: March 5, 2009Applicant: ROLLS-ROYCE PLCInventor: Michiel Kopmels
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Publication number: 20090056126Abstract: A method of manufacturing a component (110), the method comprising the steps of: providing a component having a first portion (20, 40, 60, 80, 100, 116), which first portion defines a cavity (26, 46, 66, 86, 106), characterised by; identifying a first frequency response of the first portion and/or the entire component, and introducing material (28, 48, 68, 88, 108) into the cavity to achieve an adjusted frequency response of the first portion and hence a desired frequency response of the component.Type: ApplicationFiled: July 7, 2008Publication date: March 5, 2009Applicant: ROLLS-ROYCE PLCInventors: Nigel J.D. Chivers, Keith C. Goldfinch
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Publication number: 20090057279Abstract: A method of forming an aperture in an article the method comprising the steps of directing a laser at the article and traversing the high energy beam to form a cut extending along the periphery of the aperture in a first direction to a second point on the periphery and then reversing the direction of cutting along the periphery till the aperture is formed.Type: ApplicationFiled: July 31, 2008Publication date: March 5, 2009Applicant: ROLLS-ROYCE PLCInventors: Ian M. Garry, Michael N. Wybrow
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Publication number: 20090057972Abstract: Bracing means for supporting a moveably mounted or flexible component during a machining operation that has an expandable member adapted to fit between a component and a support surface. When the expandable member is expanded a bracing member will resist movement and/or flexing of the component caused by forces arising during the machining operation. The expandable member is deformable to substantially conform to the shape of the component and the support surface.Type: ApplicationFiled: November 3, 2008Publication date: March 5, 2009Applicant: ROLLS-ROYCE PLCInventor: Brynley Clark
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Publication number: 20090057488Abstract: A method of manufacturing an aerofoil for a gas turbine engine (10). The method comprises the steps of providing first and second panels (16, 18), providing a web (30) between the first and second panels, deforming the panels by applying internal pressure between the panels so as to form an internal cavity. The method further includes the step of providing a pattern of ribs (60) on the web so as to define a aerofoil having first and second panels with at least one rib (60) forming a protrusion extending from the first panel partially across the space between the first and second panels.Type: ApplicationFiled: July 7, 2008Publication date: March 5, 2009Applicant: ROLLS-ROYCE PLCInventors: Keith C. Goldfinch, Oliver M. Strother, Julian MacKechnie-Jarvis
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Patent number: 7497073Abstract: Continuous engine monitoring with regard to gas turbine engines is difficult particularly when the engine is utilized for propulsion of an aircraft. Nevertheless, by use of transfer passages 4 to an arrangement located within the tail cone 9 of an engine, it is possible through a transparent test cell 6 and appropriate heating to generate sufficient infra red radiation as well as incandescent visible light for detectors 11, 16 to determine various constituent parts of the gas flow. Thus a photo detector 11 can provide through electrical signals, the proportion of soot/smoke particles in the gas flow through their incandescence, whilst use of filters 17 for particular spectral lines in an infra red radiation spectrum will allow detectors 16 to provide an indication through an electrical signal the proportion and presence of other constituents such as NO, CO and unburnt hydrocarbons in an exhaust gas flow.Type: GrantFiled: June 15, 2006Date of Patent: March 3, 2009Assignee: Rolls-Royce plcInventor: John D. Black
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Patent number: 7493752Abstract: A control apparatus 50 for a gas turbine engine for an aircraft includes engine control means 52 forming part of an outer fuel control loop and fuel control means/overthrust protector 76 forming part of an inner fuel control loop. Overthrust protection is provided within each of the engine control means 52 and the fuel control means/overthrust protector 76, which are powered and housed separately. Thus, a failure within one of these systems could not result in overthrust and demonstrably reliable overthrust protection is provided within a single channel.Type: GrantFiled: January 31, 2006Date of Patent: February 24, 2009Assignee: Rolls-Royce plcInventors: Michael A Horswill, Stephen G Garner
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Publication number: 20090046762Abstract: A sensor apparatus including a plurality of sensors, and a measurement device. The plurality of sensors being divided into sensor groups with each sensor group having a number of sensors. The groups being arranged such that the sensor groups are electrically matched. The sensors in a sensor group coupled in parallel with each other to form a sensor ladder. A measurement device is arranged to compare electrical signals from each sensor group and to output an indication signal, wherein the measurement device is coupled to each sensor ladder at an intermediate position and in that the coupling position of each sensor ladder are electrically equivalent to one another. Also provided by the present invention is a method of monitoring a plurality of sensors.Type: ApplicationFiled: July 22, 2008Publication date: February 19, 2009Applicant: ROLLS-ROYCE PLCInventors: David Geoffrey Henshaw, Susan Janet Riley
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Publication number: 20090044933Abstract: A heat exchanger is provided in which heat exchanger shells are formed by electro forming about a mandrel. The shells are attached and joined to provide a heat exchanger module. As the shells are not press formed problems with respect to material elongation to achieve deep grooves in the shells are potentially avoided and shells can be created with more desirable thickness to achieve more efficient heat exchange. Furthermore, reduced shell thickness will also reduce weight and therefore improve the acceptability of heat exchangers in particular applications such as those associated with aerospace and automotive sports.Type: ApplicationFiled: July 21, 2008Publication date: February 19, 2009Applicant: ROLLS-ROYCE PLCInventors: Andrew M. Rolt, Anthony G. Razzell
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Publication number: 20090047117Abstract: A flow control arrangement (30; 50; 70) is described in which an inlet slot 35, 55, 85 is positioned prior to a stationary structure (33; 43; 53; 73; 83) such as a stator or pylon in order that air flow is bled or removed from a main flow 31, 51, 81. The removed air passes through a passage duct 36, 56 and is re-injected through an outlet nozzle 37, 57, 87 with an askew angle consistent with rotor blades 32, 52, 72, 82 of a turbine. In such circumstances, distortion in the flow due to the stationary structure 33, 43, 53, 83 is relieved such that there is less instability downstream from that structure 33, 43, 53, 83.Type: ApplicationFiled: April 15, 2008Publication date: February 19, 2009Applicant: ROLLS-ROYCE PLCInventor: Liping Xu
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Publication number: 20090047853Abstract: A laminate structure (2) comprising at least a first layer (10) joined to a second layer (12) by an intermediate layer (14). The material of the first layer (10) is different to the material of the second layer (12), and the intermediate layer (14) is composed of fibres of interwoven different first (16) and second (18) materials. An adhesive (20,22) is provided between the intermediate layer (14) and at least one of the first layer (10) and second layer (12).Type: ApplicationFiled: August 12, 2008Publication date: February 19, 2009Applicant: ROLLS-ROYCE PLCInventor: Quinten J. Northfield
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Patent number: 7491032Abstract: An integrally bladed rotor is constructed from a plurality of layers of organic matrix composite material wound together in a spiral fashion to form the disc portion of the rotor, and at each rotor blade position at least the outermost one of the layers is turned substantially radially outwards from the periphery of the rotor disc to form a blade. Each blade is finished with further pieces of organic matrix composite material bonded into position on the. An encircling blade tip shroud may be formed by further layers of material wound around the tips of the blades in conjunction with closed loop inserts in the spaces between blades.Type: GrantFiled: June 23, 2006Date of Patent: February 17, 2009Assignee: Rolls Royce PLCInventors: Christopher Alan Powell, David Anthony Williams
