General Electric J85
The General Electric J85 is a turbojet jet engine of the U.S. manufacturer General Electric.
It is an engine with an eight -stage axial compressor, which produces a compression ratio of about 6,7-8:1, and a two-stage axial turbine. Without afterburner approximately 13.1 kN thrust are generated 17.1 kN with afterburner.
The engine was McDonnell ADM -20 developed as a loss of engine for the missiles, and manufactured from 1960 series. Departing from the original application, it was, for example, also, among others, at the Northrop F-5 fighter aircraft and training aircraft used Saab 105 Ö. Overall, to date more than 15,500 engines were produced, of which about 2,000 civilian derivation with the name CJ610. Good 6000 of which are still in use (4/ 2006). The supply of spare parts is to be ensured by the year 2040.
- 3.1 Technical data CF700
Specifications J85
General Electric CJ610
The civilian derivative of the J85 was announced in May 1960. It corresponds in its basic design of the J85, but does not have an afterburner. Mainly they came in models of the Learjet series to use, but also in the HFB 320 or in the IAI 1121st
The following variants were produced:
- CJ610-1/-4: First in series version. The two versions differed only in the position of the auxiliary gear.
- CJ610-5/-6: As above, but with more boost.
- CJ610-8/-9: more power, available from 1969. Use in the I.A.I. 1123.
- CJ610 -8A: The same thrust as -5, but with improved altitude performance and longer service life.
Specifications CJ610
General Electric CF700
When CF700 is also a derivative of the J85, which is used both in the civilian and military sectors. Starting with the base engine, which remained largely intact, a fan stage was added, which extends the low-pressure turbine radially. It is an aft - fan engine. Use found it standard in versions of the Sabreliner and the Dassault Falcon 20 A total of over 1100 engines this version were produced. As it can be operated vertically, it is selected as a drive for the Lunar landing training vehicle. The approval for the engine has been issued by the Federal Aviation Administration on 1 July 1964. The improved version CF700 -2D was approved in early 1968. In 1974, the MTBO be increased to 3000 h. The bypass ratio is 1.9:1, the air flow rate at 39.9 kg / s