Rolls-Royce Limited

About: Rolls-Royce Limited is a based out in . It is known for research contribution in the topics: Gas compressor & Rotor (electric). The organization has 624 authors who have published 623 publications receiving 10751 citations. The organization is also known as: Rolls Royce Limited.

Fuel burners for gas turbine engines

Abstract: Fuel is injected through very fine holes normally into a swirled airstream. A finally atomized fuel results and a solid cone of fuel and air passes into the combustion chamber. The injector gives high combustion efficiency at idle conditions reduces smoke at high power conditions.

Cooled blade for a gas turbine engine

Abstract: A cooled blade for a gas turbine engine comprises an aerofoil portion having a longitudinally extending hollow. An air entry tube is mounted within the hollow and is pressed against a locating surface within the hollow by a resilient member such as a spring tube.

Variable stator vane operating mechanism for turbomachines

Abstract: A variable stator vane operating mechanism for a gas turbine engine includes a plurality of unison rings 21,22 and 23 each connected by a drag link 18,19 and 20 respectively to a pivoting beam 14. The unison rings are connected to each of vanes 10 in a stator vane row by first arms 24. In order to minimize side loads on the unison rings by the drag links during pivoting of the beam, the beam is connected at its free end to a second arm 30 which is pivotable about an axis 28 by means of a torque tube 26 or other suitable actuator, and the length of the second arm 30 between the axis 28 and its point of connection 44 to the beam is made as nearly as possible equal to the length of the first arms 24. By this means the fore and aft movement of the beam can be matched to the fore and aft movement of the unison rings, or at least in the case of one of them, and the drag links remain substantially in the plane of the unison rings.

Turbine overspeed limiter for turbomachines

Abstract: A mechanism 25 for preventing a turbine rotor 14 from exceeding a predetermined speed if a shaft 24, connecting the turbine rotor 14 to a compressor rotor 12 of the engine, breaks and releases its axial and torsional constraint on the turbine rotor 14. The mechanism 25 comprises a segmented stator vane assembly 26 downstream of a stage of the turbine rotor 14. Each segment 26 has first and second members 38,40 projecting radially inwards. The first and second members 38,40 are provided respectively at an upstream and downstream region of the inner end of each segment 26. A constraining means 34,36 is provided to constrain the segments 26 against displacement bodily on an axial direction. Static structure of the engine 56 engages the first and second members 38,40 and provides radially outwards and axially rearwards constraint on the first members 38 and radially inwards and axially forwards constraint on the second member 40. When the shaft 24 breaks and the turbine rotor 14 strikes the structure 56 in an axial direction, the structure 56 constrains the first members 38 of each segment 26 and provides a fulcrum about which the segments 26 rotate. Simultaneously the axial and radial constraint on the second members 40 is released causing the gas loads on the segments 26 to tilt then about the fulcrum into the path of the turbine rotor blades.

Gas turbine engines

Abstract: A gas turbine engine power plant comprises a main gas turbine engine terminating in a jet pipe in which a free turbine is mounted. The free turbine is adapted to drive an auxiliary compressor. Means are provided such that a portion of the gas turbine engine efflux may be directed through the auxiliary turbine such that the auxiliary compressor augments the efflux from the main engine. Alternatively the entire gas turbine engine efflux may pass directly through the jet pipe.