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.

Development of a computer-program for the prediction of flow in a rotating cavity

Abstract: A computer program has been developed to predict laminar source-sink flow in a rotating cylindrical cavity. Although the program is based on a standard finite difference technique for recirculating flow, it incorporates two novel features. Step changes in grid size are employed to obtain sufficient resolution in the boundary layers and special treatment is given to the solution of the pressure correction equations, in the ‘SIMPLE’ algorithm, in order to improve the convergence properties of the method. Results are presented both for the flow in an infinite rotating cylindrical annulus and a finite rotating cylindrical cavity, with the inner cylindrical surface acting as a uniform source and the outer cylinder as a sink. These show good agreement with existing analytical solutions and illustrate some of the problems associated with the computation of rapidly rotating flows.

Turbine blade for gas turbine engine

Abstract: The blade has an aerofoil portion (16) having a first (23), a second (24), a third (25) and a fourth (26) internal spanwise passage for cooling air arranged in chordwise succession with the first passage being at the leading edge wall (17) of the blade. The first and third passages are connected to respective a cooling air supplies (14A,14B) at the root end (11) of the blade. At the tip (28) of the blade the third passage is connected to the second passage to introduce air, warmed on passing through the third passage, into the second passage and ameliorate undue cooling of the internal walls (19,20) between the first, second and third passages. The third passage is also connected to the fourth passage for supply of cooling air to the trailing region of the blade. The second passage has outlets (24A) to the exterior of the blade whereby the flow through the second passage is controllable independently of the air supply to the fourth passage, i.e. to the trailing region of the blade.

Fuel/oil heat exchange system for an engine

Abstract: A fuel/oil heat exchange system is proposed for an aircraft gas turbine engine for heating fuel leaving the aircraft fuel tanks before it enters the engine fuel system. The proposed system eliminates the separate fuel heater. The oil system is designed so that the fuel is not overheated at the hottest engine conditions, and the fuel/oil heat exchange system is made to increase the temperature of the oil if the fuel temperature drops below a pre-determined limit. Referring to FIG. 2 of the drawings, oil from the engine gearbox 16 is passed by scavenge pump 20 to a fuel heating coil 14 in the heat exchanger 12. Fuel from the aircraft passes through the heat exchanger prior to entering the fuel system 7 through fuel filter 6. A temperature sensing device 26 signals a reduction in fuel temperature below a desired level and closes a valve 24 preventing oil passing beneath baffle 25 to the scavenge pump. This causes the oil level to rise until oil spills over the baffle 25, at which level the gears 23 dip into the oil and churn it causing its temperature to increase.

Piezoelectric stress wave transducer with boron nitride piezo support

Abstract: A transducer for detecting stress waves comprises a piezo-electric member which is mounted on a brass backing member and carried by a boron nitride support member. The piezo-electric member is deformed under the influence of stress waves to generate an electrical output, the magnitude of which is indicative of the magnitude of the stress waves.

Propfan aircraft propulsion engine

Abstract: In a propfan engine, the need for an annular or chin-type intake when the propfan is mounted in front of the engine is avoided by mounting the propfan downstream of the engine The engine exhaust is ducted to atmosphere through inner chutes which alternate with outer chutes through which ambient air flows The alternate streams of exhaust gas and ambient air then flow through axial ducts which are located between adjacent blade mountings in the rotating hub of the propfan