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Specific fuel consumption: 0.67 lb/lbf·hr (68.3·kg/kN·h) at maximum cruising speed; Thrust-to-weight ratio: 6.6; See also. Related development. General Electric CJ610;
The Onyx2, code name Kego, is a family of visualization systems developed and manufactured by SGI, introduced in 1996 to succeed the Onyx. The Onyx2's basic system architecture is based on the Origin 2000 servers, but with the inclusion of graphics hardware. In 2000, the Onyx2 was succeeded by the Onyx 3000, and
The YJ93 started life as the General Electric J79-X275, an enlarged version of the General Electric J79 turbojet with "275" meaning Mach 2.75, the engine's target operating speed. [2] This design evolved into the X279 when Mach 3 cruise became a requirement, and ultimately became the YJ93. [3] The engine used a special high-temperature JP-6 fuel.
The P-800 Oniks (Russian: П-800 Оникс; English: Onyx), marketed in export as the Yakhont (Russian: Яхонт; English: ruby), is a Soviet/Russian supersonic anti-ship cruise missile developed by NPO Mashinostroyeniya as a ramjet version of P-80 Zubr.
However, subsequent re-designs and the incorporation of more conventional systems resulted in the engine eventually meeting the NASA requirement of 700 lbf (3,100 N) thrust. To achieve the required thrust-specific fuel consumption , the EJ22 turbofan was designed as a three spool engine having a fan, two axial compressors and three expansion ...
Includes an engine driven alternator and fuel and oil lubrication pumps. Dry weight as 18-046. Take-off thrust increased to 1.15 kN (260 lb st) and maximum continuous thrust to 1.10 kN (247 lb st). TRS 18-076 Intended for the Meteor-Mirach 100. Includes an engine driven alternator and fuel and oil lubrication pumps. Dry weight as 18-046.
The development of the engine started at Ivchenko-Progress of Zaporizhzhia, Ukraine in 1999. The engine was originally intended for the Yakovlev Yak-130 trainer aircraft. An afterburning version, the AI-222-25F (from Russian/Ukrainian term "Форсаж") is also available with thrust vectoring.
The results from the test firings of test motors SL-1 and SL-2 showed a maximum thrust value of 3.5 million pounds (15.7 meganewtons) and a burn time of 114 seconds. The firings used six tons of PBAN propellant a second, producing a column of white-hot fire visible in Miami 31 miles away. [ 8 ]