Patents Assigned to Rolls-Royce plc
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Publication number: 20100322777Abstract: A blade (2) for a compressor comprising a pressure surface (6) and a suction surface (4), wherein the suction surface (4) comprises: a discontinuity in the chord-wise curvature of an intermediate portion of the suction surface between the blade leading edge and blade trailing edge; and a slot (20) arranged along at least a portion of the blade (2) in a substantially span-wise direction, the slot (2) being disposed at or near the said change in curvature, such that when in use lower momentum fluid near the suction surface (4) is aspirated into the slot (20).Type: ApplicationFiled: June 14, 2010Publication date: December 23, 2010Applicant: ROLLS-ROYCE PLCInventors: Bronwyn POWER, Liping Xu, Steven Wellborn
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Patent number: 7854122Abstract: Apparatus for adaptive cooling comprising a first component having at least one aperture extending therethrough with a sacrificial component positioned within the at least one aperture. The first component is operable at a maximum duty temperature and the sacrificial component has a melting or sublimation point below the maximum duty temperature of the first component. The sacrificial component defines an effective aperture the size of which may be increased if, in use, the sacrificial component is subjected to a temperature between the melting or sublimation point of the sacrificial component and the maximum duty temperature of the first component.Type: GrantFiled: July 18, 2006Date of Patent: December 21, 2010Assignee: Rolls-Royce, PLCInventor: David Steele
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Patent number: 7854125Abstract: An aerofoil assembly including an aerofoil and a spray element that supplies fluid to a gas turbine engine. The aerofoil has a first part with a leading edge when located in the gas turbine engine, and a second part with a trailing edge when located in the gas turbine engine. The first part has features that slide relative to and engage with complementary features of the second part to form a releasable arrangement.Type: GrantFiled: August 15, 2007Date of Patent: December 21, 2010Assignee: Rolls-Royce PLCInventors: Gary Eadon, Andrew C. Graham
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Patent number: 7854778Abstract: An intake duct for a compressor comprises an inlet and an outlet means. The duct has a serpentine path. The outlet means comprises a first outlet and a second outlet. The duct further comprises at least one grille member configured to prevent the passage of objects over a predetermined size which is positioned in the duct out of the line of sight when viewed through the inlet. The duct is shaped such that in operation objects passing through the at least one grille member greater than a predetermined mass are directed towards the first outlet and the remainder of the objects are directed towards the second outlet. The first outlet leads overboard and/or to a trap and the second outlet leads to a compressor.Type: GrantFiled: December 16, 2005Date of Patent: December 21, 2010Assignee: Rolls-Royce, PLCInventors: Alec R. Groom, John Christopher Hacker, Jonathan Wilson, Gareth L. Jones
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Publication number: 20100314818Abstract: Over tightening of clamps (2) utilised to secure components and frames to machine tables and beds can cause significant problems with regard to damage to the bed or machine table as well as mis-location. By providing a clamp 1 having a pivot 4 and peripheral springs 2, 3 a limitation on clamping force (B) can be achieved. The clamp 1 is formed from sheet materials and incorporates an over centre pivot 4 such that the retainer 5 and in particular head 6 is brought into clamping engagement by the peripheral springs 2, 3 coming into engagement with surfaces about a slot in order to generate the clamping force (B). The peripheral springs 2, 3 come into engagement by rotation about the pivot 4 to provide a progressive clamping action.Type: ApplicationFiled: December 16, 2008Publication date: December 16, 2010Applicant: ROLLS-ROYCE PLCInventor: Paul P. Sweeting
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Publication number: 20100313404Abstract: A method and system for adjusting the clearance between a stator member and the tip of a rotor member in a rotor apparatus. The system comprises a position adjustment mechanism for adjusting the radial position of the stator member to any one of at least two and preferably three different radial positions. The system further comprises a variable pressure chamber having a first pressure state and a second pressure state. The system is arranged for applying a force for maintaining the stator member in either one of said at least two radial positions when said chamber is in said first pressure state and for allowing the position adjustment mechanism to adjust the radial position of the stator member between said at least two positions when the chamber is in said second pressure state.Type: ApplicationFiled: May 25, 2010Publication date: December 16, 2010Applicant: ROLLS-ROYCE PLCInventor: Peter R. BATES
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Publication number: 20100316486Abstract: There is disclosed a cooled component for a gas turbine engine, the component preferably taking the form of a shrouded turbine blade, and having a segment region defining a segment of an annulus for the passage of hot gases therethrough. The segment region has a pair of opposed side faces configured to lie substantially adjacent respective corresponding side faces of the segments of similar operationally and circumferentially adjacent components when a series of such components are mounted in an engine such that their respective segments define an annulus.Type: ApplicationFiled: May 24, 2010Publication date: December 16, 2010Applicant: ROLLS-ROYCE PLCInventor: Roderick M. TOWNES
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Patent number: 7850417Abstract: In a contra rotating propeller engine propeller blade assemblies are provided which rotate in opposite directions as a result of association with an epicyclic gear assembly acting as a differential gearbox. A carrier is provided to drive one propeller blade assembly. Actuators are provided to cause pitch angle adjustment of the respective propeller blades of the assemblies. These actuators, are secured upon a stationary structure and act through actuator rods and appropriate mechanisms to cause such angular pitch adjustment. Rotational de-couplers are provided to rotationally isolate the actuators while an actuator rod part acts across the assemblies and a rotational de-coupler to de-couple contra rotation between the assemblies while still allowing axial displacement for adjustment of the other propeller blade assembly.Type: GrantFiled: June 22, 2007Date of Patent: December 14, 2010Assignee: Rolls-Royce PLCInventor: David M. Beaven
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Patent number: 7850428Abstract: An aerofoil 20 for a gas turbine engine includes a root portion 22, a tip portion 24 located radially outwardly of the root portion 22, leading and trailing edges 26, 28 extending between the root portion 22 and the tip portion 24 and an internal cooling passage 34. The aerofoil 20 includes a plurality of cooling fluid discharge apertures 36 extending between the root portion 22 and the tip portion 24 in a trailing edge region 28a to discharge cooling fluid from the internal cooling passage 34 to an outer surface 31 of the aerofoil in the trailing edge region 28a and thereby provide a cooling film in the trailing edge region 28a. The cooling fluid discharge apertures 36 are arranged so that the flow rate of the cooling fluid discharged from the internal cooling passage 34 to the outer surface trailing edge region 28a varies between the root portion 22 and the tip portion 24.Type: GrantFiled: February 20, 2007Date of Patent: December 14, 2010Assignee: Rolls-Royce plcInventors: Ian Tibbott, Edwin Dane
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Patent number: 7849732Abstract: The minimum fuel flow to a combustor of a gas turbine engine is limited in response to the engine inlet temperature T1 and x, an exponent dependent on engine configuration and engine entry pressure P1, in order to provide a fuel air ratio (FAR) limit which responds to both factors. This enables the fuel flow to be limited such that the FAR is set to avoid unintentionally extinguishing the combustor flame and the rate of deceleration is maximised, regardless of ambient temperature and engine altitude.Type: GrantFiled: July 6, 2007Date of Patent: December 14, 2010Assignee: Rolls-Royce PLCInventor: Nicholas C Pashley
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Publication number: 20100307159Abstract: An improved fuel spray nozzle for a gas turbine engine is proposed, in order to address problems associated with the nozzles being wetted with fuel purged from fuel lines upon engine shutdown. The nozzle has a heat shield provided around a fuel discharge orifice, the heat shield incorporating a sliding expansion joint and having a drip collar arranged to cover the expansion joint so as to protect it from being wetted by fuel ejected through the fuel discharge orifice and falling on the heat shield. The fuel spray nozzle is particularly suited to marine or industrial gas turbine engines having a plurality of radially oriented combustion chambers with respective fuel spray nozzles.Type: ApplicationFiled: May 24, 2010Publication date: December 9, 2010Applicant: ROLLS-ROYCE PLCInventor: Ian J. Toon
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Patent number: 7845647Abstract: A gasket or seal member constructed of elastomeric material has at least one slot extending lengthwise of the member and across its thickness at an oblique angle to the sealing faces. There may be a plurality of slots spaced apart across the width of the member. In a preferred form of the invention multiple, parallel slots are formed at an oblique angle to the seal faces of the member forming branchiate-like layers of gasket material, in which each of the layers partially overlays at least one other layer.Type: GrantFiled: November 14, 2008Date of Patent: December 7, 2010Assignee: Rolls-Royce PLCInventor: Michael C. Roberts
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Patent number: 7845207Abstract: With regard to components it is necessary to test specimens of materials in order to determine acceptability for objective component performance. Previously such testing generally involved fixing and clamping of the test specimen which produced artificial stressing conditions. By providing a specimen component typically in the form of an elongate member which is suspended between mounting ends a combination is provided which has inertia. In such circumstances when a projectile impacts upon the elongate member that elongate member flexes and deforms and this deformation can be monitored for testing purposes. The projectile is arranged to have a relatively facile compliant nature upon impact with the component such that there is no local stressing of the component whilst suspending the mounting ends substantially avoids clamp resilience distorting objective or realistic stressing conditions.Type: GrantFiled: November 12, 2008Date of Patent: December 7, 2010Assignee: Rolls-Royce, PLCInventor: Simon Read
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Patent number: 7847431Abstract: Electrical power generation systems typically comprise an electrical power distribution arrangement in which a number of electrical power generators are coupled in parallel. In such circumstances in order to avoid conflict generally a first electrical power generator is controlled with a voltage controller while second electrical power generators have electrical current controllers. As loads are switched into and out of the electrical distribution system in normal operation the first electrical power generator and its voltage controller can accommodate voltage dynamics and therefore maintain a desired voltage. However, in order to accommodate heavier loads switching, the dynamic operation of the electrical current controller is achieved through utilizing operational voltage margins from a desired voltage as control signals to the electrical current controller.Type: GrantFiled: March 16, 2009Date of Patent: December 7, 2010Assignee: Rolls-Royce plcInventors: Lihua Hu, David R Trainer, Stephen A Long
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Patent number: 7845158Abstract: An engine mounting arrangement is provided in which a mounting structure is created through fins (21, 42) extended between a core (22, 46) and a mounting ring (23, 48). The fins (21, 42) have a tangential lean and substantive planar aspect in order to create an appropriate load transfer path for torque and thrust loads in an engine when secured upon a hanger mounting (20) and through utilizing further struts (25, 26) extending from spaced locations upon the mounting structure to rearward anchor positions on a pylon (27) which also has the hanger mounting (20) attached.Type: GrantFiled: October 25, 2007Date of Patent: December 7, 2010Assignee: Rolls-Royce PLCInventor: Kenneth F. Udall
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Publication number: 20100303635Abstract: Providing cooling within hollow blades such as high pressure turbine blades in a gas turbine engine is important to maintain these components within operational margins for the materials from which they are formed. Traditionally, coolant flows in hollow passages have been used along with impingement apertures towards a leading passage for cooling effectiveness. It is known that opposed undulations or ribs can create rotational vortices within the passage. By shaping shaped portions between the opposed undulations and possibly providing undulations upon these shaped portions themselves it is possible to generate stronger more powerful vortices within the passage. These vortices are coupled with the impingement orifices to create proportionally greater impingement jet flow and pressure and therefore cooling effectiveness within the leading passage.Type: ApplicationFiled: May 26, 2010Publication date: December 2, 2010Applicant: ROLLS-ROYCE PLCInventors: Roderick M. TOWNES, Ian Tibbott, Edwin Dane, Caner H. Helvaci
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Publication number: 20100301158Abstract: An aircraft having a lift/propulsion unit which includes a power unit such as a turboshaft engine which drives a fan through a transmission mechanism. The fan discharges to vectoring nozzles which can be independently swivelled to provide lift or propulsion thrust. An output shaft of the transmission mechanism serves as the main shaft of a motor/generator of modular form. The motor/generator can act as a generator to charge an electrical storage device such as a battery, or as a motor to drive the fan, either alone or to supplement the output of engine. Reaction control nozzles are provided at extremities of the aircraft to provide stabilising thrust. The aircraft is capable of vertical take off and hovering, with the vectoring nozzles swivelled to a lift position, and forward thrust with the vectoring nozzles swivelled to a propulsion position.Type: ApplicationFiled: April 15, 2010Publication date: December 2, 2010Applicant: ROLLS-ROYCE PLCInventors: Paul J.H. HARRIS, Frank A. Hewitt, Martin C. Johnson, Christopher Wright
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Publication number: 20100303616Abstract: A cooling system is provided for an aero gas turbine engine. The system has a duct which diverts a portion of a bypass air stream of the engine. A heat exchanger located in the duct receives cooling air for cooling components of the engine. The cooling air is cooled in the heat exchanger by the diverted bypass air stream. After cooling the cooling air, the spent diverted air stream is routed to a tail cone located at the exit of the engine and ejected through a nozzle at the tail cone.Type: ApplicationFiled: February 12, 2010Publication date: December 2, 2010Applicant: ROLLS-ROYCE PLCInventors: Adam P. Chir, Andrew M. Rolt
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Patent number: 7841060Abstract: A method for joining components comprises locating a region, such as an end region 24, of a shape memory alloy (SMA) material component 10 adjacent to a further component 12, and generating localized plastic deformation of the aforesaid region to create a joint between the components 10, 12. The localized plastic deformation of the shape memory alloy material component 10 is preferably generated by applying a shock load to the shape memory alloy material component 10.Type: GrantFiled: October 16, 2006Date of Patent: November 30, 2010Assignee: Rolls-Royce plcInventors: Daniel Clark, John R Webster
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Patent number: 7843354Abstract: A determination of bleed valve activation in a gas turbine engine can be difficult unless the engine is maintained at a steady idle state for comparison between that state and effects of activation of the bleed valve. Furthermore, specific test activation of bleed valves increases wear and tear on those valves. By sensing a flow pressure response signal and then through appropriate averaging and processing through a non-linear filter, it is possible to identify bleed valve activation by a target signal response exceeding a threshold indicative of such bleed valve activation.Type: GrantFiled: September 5, 2007Date of Patent: November 30, 2010Assignee: Rolls-Royce PLCInventors: Jonathan Edmund Holt, Richard Leonard Martin
