Pratt & Whitney Canada JT15D
The Pratt & Whitney Canada JT15D is a turbofan jet engine of the Canadian manufacturer Pratt & Whitney Canada in a two -shaft design. Technical features include a radial high pressure compressor and the reversing combustion chamber.
Development
The impetus for the development of this engine was a 1965 study carried out on the future demand for small jet engines. Then began in June 1966 with the design of a compact fan engine with a target thrust from 8.9 to 11.12 kN. Further development goals were the lowest possible number of parts, a compact design, low generation costs and maintenance costs, low noise generation, high reliability and a low specific fuel consumption. The first run of the new engine took place on 23 September 1967.
Use
It was used first at the twin Cessna Citation. First prototype engines were delivered in August 1969 at Cessna. From the 1972 series produced and used in the Citation design JT15D -1 and -1A total of 1417 engines have been delivered.
Then came the uprated version JT15D -4 used for the Cessna Citation II. Your serial production began in 1973. It was also built at the Mitsubishi Diamond, the Aerospatiale SN 601 and the Agusta S211. A total of 2195 pieces of this version were delivered.
The successor JT15D -5 in 1983 was awarded his license and was used in the Raytheon Hawker 400XP, the military Cessna T- 47A and in the Scaled Composites ARES. Several subtypes were manufactured only slightly differed from the original pattern. The execution JT15D -5A was also in the Cessna Citation V for use, the JT15D -5B in the military version of the Beechcraft T -1A Jayhawk, and the JT15D -5C finally in the Rockwell Ranger 2000 and Agusta S211A.
The latest version is the 1993 presented JT15D - 5D, which has a fan housing made of Kevlar, a fan in blisk technology and a high pressure turbine with blades made of single crystals. It is used in the Cessna Citation Ultra. In the Raytheon Beech TCX JT15D -5F used.
Technical design ( JT15D -1)
The JT15 are two-shaft turbofan engines. The air enters the fan leitschaufellosen one who, in his interpretation of the Pratt & Whitney JT9D corresponds to, but is much smaller. The air flow for the core engine is then fed through a radial compressor stage of the combustion chamber. The execution JT14D -4 has in addition a single axial stage before the centrifugal compressor, but a smaller fan and also a reduced bypass ratio. The compressed air passes in accordance with the radial step in the reversing annular combustion chamber, where it undergoes a change in direction by 180 °. The fuel is injected at a pressure of up to 44.8 bar in the combustion chamber. After the combustion chamber is effected a further deflection of the hot gas of 180 ° in the direction of the turbine stages. The high-pressure turbine stage, performed the low-pressure turbine in two stages. The exhaust nozzle has a central cone which can be displaced axially in order to change the outlet cross section, depending on the power setting. The auxiliary devices are of a shaft which is connected to the high -pressure turbine shaft, is driven. You are in the front area of the engine. The pressure oil is supplied by a gear pump. The lubrication pressure is, in operation at 5.52. For starting, an air turbine or an electric starter is used, it is ignited by electric spark plugs 2.