Patents Assigned to Roll-Royce Deutschland Ltd & Co KG
  • METHOD FOR DETERMINING A FLOW BEHAVIOUR OF A MEDIUM
    Publication number: 20130124114
    Abstract: A method for determining a flow behavior of a medium uses at least one analysis device placed inside the medium. The at least one analysis device is freely moveable in the medium and supplies data characterizing at least one property of the medium flow behavior to a data evaluation device. The at least one property of the medium flow behavior is determined by the data evaluation device on the basis of the data in selected areas or in all areas through which the at least one analysis device flows with the medium.
    Type: Application
    Filed: November 15, 2012
    Publication date: May 16, 2013
    Applicants: ROLLS-ROYCE PLC, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Rolls-Royce Deutschland Ltd & Co KG, Rolls-Royce plc
  • Turboprop propulsion unit with pusher propeller
    Patent number: 8438829
    Abstract: A turboprop propulsion unit includes at least one pusher propeller 5, 6 driven by an aircraft gas-turbine engine, with the aircraft gas-turbine engine being arranged in front of the pusher propeller 5, 6 in a direction of flight. A turbine outlet area 9 is arranged at the front in the direction of flight and a compressor area 14 faces towards the pusher propeller 5, 6.
    Type: Grant
    Filed: February 24, 2010
    Date of Patent: May 14, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Dimitrie Negulescu
  • Flow divider having breaking points for a fan engine
    Patent number: 8438828
    Abstract: A flow divider (1) for a fan engine which forms an annular leading edge (4) simultaneously on the outer circumference of an annular core air duct and the inner circumference of an annular secondary air duct, protrudes into the fan airflow and has an aerodynamic profile. In order to avoid blockage of the core air and/or secondary air ducts in the event of destruction or detachment of the flow divider (1), the flow divider features separable parts (6) which, whatever their orientation, are capable of passing the vane passages of the core air duct and the secondary air duct.
    Type: Grant
    Filed: December 4, 2009
    Date of Patent: May 14, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Olaf Lenk
  • Engine blade with excessive leading edge loading
    Patent number: 8439646
    Abstract: A free end of a blade of a fluid flow machine has a skeleton line camber distribution having an excessive value to a relative skeleton line camber of at least ?*=0.35 for a related running length of s*=0.1 in a blade profile flow line section between the free end and a blade section at 30% of a main flow path width from the free end. S* is a local running length relative to a total running length of the profile skeleton line and ?* is an angular change of the skeleton line relative to a total camber of the skeleton line from a leading edge to a related running length s*. The skeleton line camber distribution runs between leading edge point V (s*=0, ?*=0) and trailing edge point H (s*=1, ?*=1).
    Type: Grant
    Filed: June 14, 2010
    Date of Patent: May 14, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • ACCESSORY GEARBOX DEVICE FOR A JET ENGINE
    Publication number: 20130098179
    Abstract: The present invention proposes an accessory gearbox (9) for an engine with a drive shaft (12) operatively connectable to a main shaft of the engine, with an extension shaft (29) being provided which can be put into a detachable operative connection to the drive shaft (12) substantially coaxially to said drive shaft (12) of the accessory gearbox (9). At least one auxiliary unit (39) can be detachably arranged on the extension shaft (29).
    Type: Application
    Filed: August 23, 2012
    Publication date: April 25, 2013
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Juergen BEIER, Gideon VENTER
  • Fan casing for a jet engine
    Patent number: 8425178
    Abstract: A fan casing (2) for a jet engine has a burst protection arrangement (7) made up of layers at least in an area of fan blades (5). To contain detached fan blades (5) within a fan casing (2) of a jet engine by use of a low-weight and easily manufacturable burst protection arrangement (7), the fan casing (2) is made of a fiber-composite material which itself forms at least one layer provided with at least one inorganic, non-metallic protective layer (8).
    Type: Grant
    Filed: December 16, 2009
    Date of Patent: April 23, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Olaf Lenk
  • METHOD FOR REPAIRING ROTOR BLADES
    Publication number: 20130091704
    Abstract: In a method for repairing worn or damaged rotor blades of an aircraft engine, laser cladding for the reconstruction of the blade tips is not performed in a continuous welding process along the blade edge but during a cycle-by-cycle rotation of the rotor blades attached to a rotor disk, in only one limited section of the respective blade edge for each cycle. The method reduces time expenditure for the repair of the blades and improves the tribological properties of the blade material in the area of the repaired blade tip.
    Type: Application
    Filed: May 30, 2011
    Publication date: April 18, 2013
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Josef Nebesni
  • Fluid flow machine featuring an annulus duct wall recess
    Patent number: 8419355
    Abstract: A fluid flow machine has a flow path provided by a casing (1) and a rotating shaft (2), in which rows of rotor blades (3) and stator blades (4) are arranged, and includes at least one annular groove-type recess (5) being disposed in a blade (3, 4) tip area in an annulus duct wall of the casing (1) and/or the shaft (2). An upstream end point (E) of the recess (5) in a flow direction is set at a distance (e)>0 forward of a forward blade tip point (A), and a downstream end point (F) of the recess (5) is set at a distance (f) rearward of point (A), where: 0.5 L>(f)>0, and L is a distance between point (A) and a rearward blade tip point (B).
    Type: Grant
    Filed: August 11, 2008
    Date of Patent: April 16, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Volker Guemmer, Marius Swoboda
  • GAS TURBINE COMBUSTION CHAMBER ARRANGEMENT OF AXIAL TYPE OF CONSTRUCTION
    Publication number: 20130086908
    Abstract: A gas-turbine combustion chamber arrangement includes a flame tube, a diffuser element arranged upstream of the flame tube in the flow direction, the diffuser element including an annular duct, and an axial compressor arranged upstream of the diffuser element. The diffuser element features an annular guide vane area in which guide vanes are arranged, which for redirecting an incoming flow are provided at an angle (?) in a range between 28° and 32° relative to a central axis of the gas turbine. Downstream of the guide vane area, a diffuser area is arranged, the diffuser area not being provided with flow-guiding elements affecting the flow, where burners arranged in the annular combustion chamber are provided with their burner axes at an angle (?) between 40° and 50° relative to the central axis.
    Type: Application
    Filed: June 15, 2011
    Publication date: April 11, 2013
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Dimitrie Negulescu
  • Scoop of a running-gap control system of an aircraft gas turbine
    Patent number: 8408008
    Abstract: A scoop for a fairing 1 of a core engine 2 of an aircraft gas turbine allows air to be supplied from a bypass flow in a bypass duct 3 to several cooling-air distributors in a core-engine ventilation compartment 4. The scoop includes a first tubular flow duct 5, whose inlet opening 6 is arranged in the bypass duct 3 and which extends through the fairing 1, as well as a second tubular flow duct 7, which at least partly encompasses the first flow duct 5 and whose inlet opening 8 is rearwardly offset relative to the inlet opening 6 of the first flow duct 5 in the direction of flow.
    Type: Grant
    Filed: March 3, 2010
    Date of Patent: April 2, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Predrag Todorovic, Stephan Herzog, Christian Seydel
  • Blade variation in dependence of the degree of throttling on fluid-flow machine
    Patent number: 8403621
    Abstract: A method for the variation of at least one blade row of a fluid-flow machine, in which, in dependence of the actual operating point, in addition to an aerodynamic speed, at least one further quantity pertinent to the position of the operating point in the family of characteristics of the fluid-flow machine is employed for control.
    Type: Grant
    Filed: March 13, 2008
    Date of Patent: March 26, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • Blade shroud with fluid barrier jet generation
    Patent number: 8403630
    Abstract: A fluid flow machine has a main flow path, in which at least one row of blades (1) is arranged, and a shroud (2), which is embedded in a recess (3) of a component, with the component and the blades (1) being in relative rotational movement to each other. The assembly forming the shroud includes at least one internal chamber (7) which is suppliable with fluid from a source. The at least one internal chamber (7) is connected to the main flow path surrounding the blades (1) or to a cavity (9) surrounding the shroud (2) via at least one outlet (8) which is arranged on one side of the shroud (2). The shape of the outlet (8) and the shape of the outlet opening are such that a fluid barrier jet is generated at the outlet (8), which stops recirculation of fluid through the shroud cavity (9).
    Type: Grant
    Filed: August 11, 2008
    Date of Patent: March 26, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • Aircraft propulsion unit in multi-fan design
    Patent number: 8402740
    Abstract: An aircraft propulsion unit includes a gas-turbine core engine 10 having at least one compressor, one combustion chamber and one turbine driving a main shaft 11. The main shaft 11 of the gas-turbine core engine 10 is operationally connected to at least two separate fans 6-9 via a mechanical drive connection, each of them being arranged beside the gas-turbine core engine 10.
    Type: Grant
    Filed: February 27, 2009
    Date of Patent: March 26, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • GENERATOR AND ACCESSORY GEARBOX DEVICE WITH A GENERATOR
    Publication number: 20130057093
    Abstract: The present invention proposes a generator for arrangement on a shaft of an accessory gearbox of an engine with a stator and with a rotor which can be coupled to a shaft of the accessory gearbox of the engine and which is rotatably mounted relative to the stator, where a stator area receiving the stator can be separated from a rotor area receiving the rotor. The rotor can be supplied with cooling medium in the rotor area. It furthermore proposes an accessory gearbox of an engine with a drive shaft operatively connectable to a main shaft of the engine and with at least one generator arranged on a shaft of the accessory gearbox.
    Type: Application
    Filed: August 23, 2012
    Publication date: March 7, 2013
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Juergen BEIER, Soeren BRAUN
  • Gas-turbine combustion chamber with a holding means of a seal for an attachment
    Publication number: 20130055716
    Abstract: Gas-turbine combustion chamber with a combustion chamber head made from a metallic material and mounting at least one burner, and with a combustion chamber wall made from a ceramic material, where at least one igniter plug or other combustion chamber attachments such as acoustic dampers, sensors or valves are arranged in a recess of the combustion chamber wall, and where in the area of the recess a seal is arranged that is mounted by means of a metallic holding means from another component than the CMC combustion chamber wall.
    Type: Application
    Filed: April 11, 2012
    Publication date: March 7, 2013
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Miklos GERENDAS
  • Fluid flow machine
    Patent number: 8382422
    Abstract: A fluid flow machine has a main flow path 2 which is confined by a hub 3 and a casing 1 and in which at least one row of blades 5 is arranged. A gap 11 is provided on at least one blade row 5 between a blade end and a main flow path confinement, with the blade end and the main flow path confinement performing a rotary movement relative to each other. At least one reversing duct 7 is provided in the area of the blade leading edge in the main flow path confinement at a discrete circumferential position. The reversing duct 7 connects two openings 12, 13 arranged on the main flow path confinement.
    Type: Grant
    Filed: August 3, 2009
    Date of Patent: February 26, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • Blade of a turbomachine with enlarged peripheral profile depth
    Patent number: 8382438
    Abstract: A blade for an axial-flow turbomachine with a gap-side blade area I which transits into a free blade end and with a hub-side or casing-side blade area II, respectively. Blade 3 forms a flow line profile section with leading edge VK and trailing edge HK which establish forward end point V and rearward end point H, respectively, by a tangent normal to and intersecting with the profile chord, with the distance between these end points being profile depth L. Blade 3 includes an enlargement of profile depth L at a tip of the free blade end which is at least +10 percent and decreases to zero in the blade central section, with the values being non-negative throughout, with the profile enlargement at trailing edge HK being larger than zero at the tip in the gap-side peripheral section.
    Type: Grant
    Filed: November 28, 2005
    Date of Patent: February 26, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Volker Guemmer
  • METHOD FOR THE MANUFACTURE OF A COMPONENT FOR HIGH THERMAL LOADS, A COMPONENT PRODUCIBLE BY THIS METHOD AND AN AIRCRAFT ENGINE PROVIDED WITH THE COMPONENT
    Publication number: 20130045093
    Abstract: A method for manufacturing a thermally deformable component for high thermal loads, includes: providing a first area of the component with a first metallic material by a generative laser process, or making the first area of the first metallic material; providing a second area of the component with a second metallic material by a generative laser process, or making the second area of the second metallic material; where at least one of the metallic materials is deposited by the generative laser process, and a ratio of a linear expansion coefficient ?1 of the first metallic material and of a linear expansion coefficient ?2 of the second metallic material is as: ? 2 ? ( T 2 ) ? 1 ? ( T 1 ) = x ? ? T 1 - T 0 ? ? T 2 - T 0 ? , where x=0.5 to 1; T1=mean operating temperature on a hot side; T0=reference temperature; T2=mean operating temperature on a cold side.
    Type: Application
    Filed: August 17, 2012
    Publication date: February 21, 2013
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Thomas WUNDERLICH, Dan ROTH-FAGARASEANU, Susanne GEBHARD
  • COMBUSTION CHAMBER HEAD OF A GAS TURBINE WITH COOLING AND DAMPING FUNCTIONS
    Publication number: 20130042627
    Abstract: A combustion chamber head of a gas turbine has a substantially annular combustion chamber outer wall 18 as well as a substantially annular combustion chamber inner wall 42 and several burners 6 distributed around the circumference. The combustion chamber head 5 has an inflow-side wall 13 which together with a wall 14 facing the combustion chamber 7 forms a combustion chamber head volume 15. The inflow-side wall 13 is provided with at least one inflow opening 32, the wall 14 facing the combustion chamber 7 is provided with at least one outflow opening 17 for connecting the combustion chamber head volume 15 to the combustion chamber 7, and at least one cooling air duct 29 is provided in the wall 14 facing the combustion chamber 7. A method for cooling and damping of the combustion chamber head is also disclosed.
    Type: Application
    Filed: August 16, 2012
    Publication date: February 21, 2013
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Miklos GERENDAS, Sermed SADIG, Jochen BECKER, Jonathan F. CARROTTE, Jochen RUPP
  • Method for the manufacture of metallic components
    Patent number: 8375542
    Abstract: When manufacturing slender metallic components (9) by cutting shaping from pre-manufactured forgings (1), the respective component (9) upon finish machining by cutting is dimensionally inspected to determine deformations (a) induced by manufacture, as compared to the nominal position, and on the basis of the measuring result the position of tensile stress areas (4) in rim layers of the component (9) is determined. For positionally balancing the component (9), the tensile stress areas (4) causing deformation of the component (9) are subjected to controlled shot peening at a specified intensity.
    Type: Grant
    Filed: July 27, 2009
    Date of Patent: February 19, 2013
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Rainer Mielke