J79 engines may be started using compressed air directly on the engine turbine blades [15] or by using a turbine starter attached to the accessory gearbox. The gas used in this starter is either compressed air or from a solid propellant cartridge.

Variable-pitch stator blades adjust automatically to (1) reduce stall problems at low engine speeds, (2) give maximum compressor efficiency under all flight conditions and (3) to match engine and airframe induction system for good stall margin at high airplane speeds.

The J79 is a single-spool turbojet with a seventeen-stage compressor with a novel arrangement of variable stator blades which allow the engine to develop pressure similar to a twin-spool engine at a much lower weight. Each blade is made largely of stainless steel.

Engine-Tested Composite Compressor Blades We accomplished something that has never been done before with composites: we manufactured and tested our first composite compressor blades in a GE J79 fighter jet engine!

Jul 20, 2007 · The compressor blade on J79 engine has been investigated to determine the cause of failure. The vibration and sounds were recognized by the pilot during take off, the RPM dropped 72%, and some flare at the rear engine was observed by the run way control tower.

The General Electric J79 engine was a high-performance single-shaft turbojet that featured variable-incidence stator blades in the later high-pressure stages of its seventeen-stage compressor.

J79-1E-1 StandardAero offers industry-leading maintenance, repair and overhaul services for legacy engines, including the J79-E1-1. The GE J79 axial flow turbojet engine was built for use in a variety of fighter and bomber aircraft and a supersonic cruise missile. The J79 was produced by General Electric Aircraft Engines in the United States, and under license

The J79 engine is a single flow, single shaft engine with an afterburner. The engine starts with a cone with a turbo starter. There are eight fixed blades in the inlet, which organize the air flow.

On November 6, 1958, Germany decided to fly the F-104G powered by the J-79-GE-11A axial flow, turbojet engine, with afterburner. Major components of the engine are a 17-stage compressor section, an accessory drive section, a combustion section, a 3-stage turbine, a high-trust afterburner, and a variable-area exhaust nozzle.

After normal engine usage of 5 months, the blade fractured and blade fragments hit the other compressor blades, stators, and casing, and caused damage in both combustion and turbine sections. The compressor blade on J79 engine has been …