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The Rolls-Royce BR700 is a family of turbofan engines for regional jets and corporate jets. It is manufactured in Dahlewitz, Germany, by Rolls-Royce Deutschland: this was initially a joint venture of BMW and Rolls-Royce plc established in 1990 to develop this engine. The BR710 first ran in 1995. [1]
Rolls-Royce AE 3007; Rolls-Royce BR700; Rolls-Royce/MAN Turbo RB.193; Rolls-Royce RB211; Rolls-Royce RB401; Rolls-Royce Trent; Rolls-Royce Trent 500; Rolls-Royce Trent 700; Rolls-Royce Trent 800; Rolls-Royce Trent 900; Rolls-Royce Trent 1000; Rolls-Royce Trent 7000; Rolls-Royce Trent XWB
The $680 million sale was approved by the US State Department on October 7, ... Powerplant: 2 × Rolls Royce BR700-710 C4-11 turbofan, 15,385 lbf (68.44 kN) ...
Rolls-Royce remains active as a major supplier to IAE. During 2011, both Rolls-Royce and Pratt & Whitney proposed establishing a new joint venture to develop engines for future generation mid-size aircraft (120-230 passengers); [ 16 ] however, during late 2013, it was announced that the two firms had decided to forego such a collaboration in ...
Rolls-Royce based the ten-stage high-pressure compressor on an eight-stage run in the RB401 in the mid 1970's followed by a nine-stage run in the RJ.500. The V.2500 would use ten stages, with the first four with variable stators, giving a pressure ratio of 20:1. [4] A single-stage booster was also part of the original configuration.
The Rolls-Royce AE 3007 (US military: F137) is a turbofan engine produced by Rolls-Royce North America, sharing a common core with the Rolls-Royce T406 (AE 1107) and AE 2100. The engine was originally developed by the Allison Engine Company , hence the "AE" in the model number.
The Rolls-Royce/MAN Turbo RB.193 is a vectored thrust turbofan engine designed and manufactured by Rolls-Royce and MAN Turbo in the mid-1960s. The engine test flew in its sole application, the VFW VAK 191B VTOL fighter aircraft but production did not follow after cancellation of the associated aircraft project.
The GE Passport is a high bypass ratio turbofan. The engine is a twin-spool, axial-flow turbofan with a high bypass ratio of 5.6:1 and an overall pressure ratio of 45:1. The front fan is attached to the three-stage low-pressure compressor; the 23:1 pressure ratio 10-stage high-pressure compressor includes five blisk stages for weight reduction.
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