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 control systems for gas turbine engines

Abstract: A fuel control system for a gas turbine engine for an aircraft comprising two modes of operation, a first mode in which the net thrust of the engine increases with an increase in the forward speed of the aircraft and a second mode in which the net thrust of the engine is caused to decrease with an increase in the forward speed of the aircraft, a selectively operable control device such as a valve or a valve with a least wins device being provided for selecting one of the modes of operation at a time.

Fluid flow ducts

Abstract: A fluid flow duct of a gas turbine engine, the duct being defined between a fan cowl and a centrebody and there being provided movable flexible members attached to the centrebody; each member being movable within the duct by fluid pressure between a first concave position and a second convex position for varying the cross-sectional flow area of the duct.

Strain gauge simulator

Abstract: In order to facilitate the accurate calibration of a strain gauge amplifier, an electrical circuit is provided, the output of which simulates the output of a strain gauge. A given polarizing current which is the same as that normally applied to the strain gauge is applied to the electrical circuit. Additional, circuitry is provided for producing a single electrical output equivalent to that of the strain gauge.

The Effect of Reynolds Number and Velocity Distribution on LP Turbine Cascade Performance

Abstract: Because of the laminar boundary-layer’s inability to withstand moderate adverse pressure gradients without separating, profile losses in LP turbines operating at low Reynolds numbers can be high. The choice of design pressure distribution for the blading is thus of great importance.Three sub-sonic LP turbine nozzle-guide-vane cascade profiles have been tested over a wide range of incidence, Mach number and Reynolds number. The three profiles are of low, medium and high deflection and, as such, display significantly different pressure distributions. The tests include detailed boundary-layer traverses, trailing-edge base-pressure monitoring and oil-flow visualisation.It is shown that the loss variation with Reynolds number is a function of pressure distribution and that the trailing-edge loss component is dominant at low Reynolds number. The importance of achieving late flow transition — rather than separation — in the suction-surface trailing-edge region is stressed.The paper concludes by remarking on the advantages and practical implications of each loading design.Copyright © 1986 by ASME