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The Allison T56 is an American single-shaft, modular design military turboprop with a 14-stage axial flow compressor driven by a four-stage turbine. It was originally developed by the Allison Engine Company for the Lockheed C-130 Hercules transport [3] entering production in 1954.
Data from The Instrumentation Design And Control of a T63-A-700 Gas Turbine Engine General characteristics Type: Turboshaft Length: 40.5 in (1,029 mm) Diameter: 22.5 in (572 mm) Dry weight: 138.5 lb (63 kg) dry Components Compressor: 6-stage axial + 1-stage centrifugal compressors Combustors: Single can combustion chamber Turbine: 2-stage axial gas generator power turbine + 2-stage axial free ...
The Allison T56 turboprop engine has been developed extensively throughout its production run, the many variants are described by the manufacturer as belonging to four main series groups. Initial civil variants (Series I) were designed and produced by the Allison Engine Company as the 501-D and powered the Lockheed C-130 Hercules .
On July 11, 1989, Saab-Scania A.B. selected the GMA 2100 to power its new Saab 2000, a 50-seat stretch of the Saab 340 turboprop, in a US$500 million deal. [2] In July 1990, Industri Pesawat Terbang Nusantara (IPTN) of Indonesia picked the GMA 2100 as the engine for the twin-engine N-250 regional airliner. [3]
The T40 concept originated at Allison in 1944, where design studies were carried out on a 4,000 shp (2,983 kW) turboprop engine. Taking advantage of this effort, the US Navy awarded Allison a contract for the design and development of a 4,100 shp (3,057 kW) turboprop engine.
The Allison T38 (company Model 501) was an early turboprop engine developed by Allison Engine Company during the late 1940s. The T38 became the basis for the very successful family of Allison T56 turboprop engine.
The Navy and Allison signed a formal contract on 2 May 1986, and the first engine to test ran six months after. [7] The T406 is based on the Allison T56 turboprop from the P-3 and the C-130, with the free power turbine of the Allison T701 turboshaft from the defunct Heavy Lift Helicopter program.
Data from 1966 Aerospace Year Book, page 497 General characteristics Type: Turboprop Length: 160 in (4,100 mm) Diameter: 35 in (890 mm) Dry weight: 1,565 lb (710 kg) Components Compressor: 14-stage with variable geometry vanes Turbine: 4-stage Performance Maximum power output: 4,125 shp (3,076 kW) Overall pressure ratio: 11.7 See also Aviation portal Related development Allison Model 250 -E3 ...