Rolls-Royce Motor Cars

About: Rolls-Royce Motor Cars is a based out in . It is known for research contribution in the topics: Turbine & Gas compressor. The organization has 3845 authors who have published 4934 publications receiving 58973 citations. The organization is also known as: Rolls-Royce Motor Cars Limited.

Measurement of strain in a titanium linear friction weld by neutron diffraction

Abstract: We report measurements of strain by pulsed neutron diffraction in a titanium linear friction weld as a function of distance from the weld zone. While the average strains in a particular direction follow continuum mechanics expectations, examination of strains in different crystallographic directions highlights the process of grain reorientation undergone during the welding.

Vehicle air conditioning system

Abstract: The invention concerns a vehicle air conditioning system comprising an air intake, a refrigerant evaporator, a heater and a heater by-pass conduit, first and second outlet ducting for separately conveying air to respective outlets in the upper and lower parts of the vehicle interior respectively, air-mixing means associated with each said outlet ducting and which is automatically settable to feed to the said outlet ducting air which has passed through the evaporator and selectively through the heater and the heater by-pass conduit, settable mass flow regulating means in each said outlet ducting, air temperature sensing means adapted to measure the air temperature in the respective outlet ducting, the ambient temperature, and the temperature inside the vehicle, and adapted automatically to control the air-mixing means and the mass flow regulating means, means for closing the outlet of the second outlet ducting and diverting the entire output of the system to the first outlet ducting, and a manual device for varying the setting of the said sensing means.

The Influence of Shrouded Stator Cavity Flows on Multistage Compressor Performance

Abstract: Experiments were performed on a low-speed multistage axial-flow compressor to assess the effects of shrouded stator cavity flows on aerodynamic performance. Five configurations, which involved systematic changes in seal-tooth leakage rates and/or elimination of the shrouded stator cavities, were tested. Rig data indicate increasing seal-tooth leakage substantially degraded compressor performance. For every 1 percent increase in seal-tooth clearance-to-span ratio, the decrease in pressure rise was 3 percent and the reduction in efficiency was 1 point. These observed performance penalties are comparable to those commonly reported for rotor and cantilevered stator tip clearance variations. The performance degradation observed with increased leakage was brought about in two distinct ways. First, increasing seal-tooth leakage directly spoiled the near-hub performance of the stator row in which leakage occurred. Second, the altered stator exit flow conditions, caused by increased leakage, impaired the performance of the next downstream stage by decreasing the work input of the rotor and increasing total pressure loss of the stator. These trends caused the performance of downstream stages to deteriorate progressively. Numerical simulations of the test rig stator flow field were also conducted to help resolve important fluid mechanic details associated with the interaction between the primary and cavity flows. Simulationmore » results show that fluid originating in the upstream cavity collected on the stator suction surface when the cavity tangential momentum was low and on the pressure side when it was high. The convection of cavity fluid to the suction surface was a mechanism that reduced stator performance when leakage increased.« less

Heat shield arrangement for a gas turbine combustion chamber

Abstract: In order to cool the hot surface of the heat shield that surrounds the burner of a gas turbine annular combustion chamber as efficiently as possible, especially in the vicinity of the burner throughflow opening, a cooling air stream that escapes through a ridge that runs around the edge of the throughflow opening is guided by a guide rib in the direction of the throughflow opening. This guide rib is aligned essentially parallel to the ridge and on the combustion chamber side has an end that is bent in such fashion that the cooling air stream that flows into the gap between the ridge and the guide rib is deflected thereby in the direction of the hot surface of the heat shield.