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.

Design of New Three Stage Low Pressure Turbine for the BMW Rolls-Royce BR715 Turbofan Engine

Abstract: In 1990, BMW and Rolls Royce plc (RR) joined to form a new company BWW-Rolls-Royce GmbH (BRR), to develop the BR700 family of engines aimed at the 12K and 25K lbs thrust range, using advanced technology and a modern organisation working in integrated teams to minimise the engine development timescales. After a successful development programme the BR710 engine rated at 14K lbs thrust, will shortly enter service in Gulfstream and Canadair Executive Jets.The recent launch of the BR715 engine at 21K lbs thrust, builds on the high pressure core developed for the BR710, plus a low pressure system with an increased diameter fan and 2 stage booster driven by a three stage turbine.This paper will describe, the advanced design technology incorporated, including the latest three dimensional aerodynamic philosophy using advanced high lift aerofoils for reduced parts count, plus the mechanical design issues addressed to optimise the LP turbine module configuration and the simultaneous design/make process employed to achieve the required parts delivery timescales.Copyright © 1997 by ASME

Blade track assembly with turbine tip clearance control

Abstract: A turbine shroud assembly or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud assembly includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.

TIME RESOLVED MEASUREi.lENTS OF A TURBINE IROTUR STATIONARY TIP CASING PRESSURE AND HEAT Tt?AN!IFER FIELD

Abstract: This paper presents the results of a detailed experimental investigation of the time resolved heat transfer rate and static pressure distribution on the stationary casing above the tip of a transonic high pressure turbine rotor in a short duration turbine test rig (the NIT Blowdown Turbine Facility), which reproduced all of the full scale. non-dimensional turbine operating parameters. Measurements were made as a function of rotor corrected speed and of Reynolds No. is shown to be highly unsteady with fluctuations of 80% across the blade spacing. Approximately 45% of the total heat load to the shroud is from the flow under the blade tip. The time averaged heat flux to the casing drops by a factor of 5 down the blade chord and is shown to vary as Re0.8. the flow in the tip region is primarily influenced by the pressure loading across the blade. The heat flux