F100-pw-100 (f-15a/b/c/d) Aircraft Engine Parts

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Part Number
NSN
NIIN
0102-6-4B Pipe Bushing
002026491
0119928 Pipe Bushing
002026491
015-90010-58 Pipe Bushing
002783167
0187-3-4X1-2 Pipe Bushing
002783167
06110-0604 Pipe Bushing
002026491
0716-MM5 Pipe Bushing
002783167
0716-MM5-J10 Pipe Bushing
002783167
08505-008 Pipe Bushing
002026491
100061-009 Pipe Bushing
002783167
1001116 Pipe Bushing
002026491
100178 Pipe Bushing
002026491
103-2 Pipe Bushing
002026491
103-22604 Pipe Bushing
002026491
10501658 Pipe Bushing
002783167
10553100-4 Pipe Bushing
002026491
10596 Pipe Bushing
002026491
110-3/8X1/4 Pipe Bushing
002026491
110-B-12X08 Pipe Bushing
002783167
11089 Pipe Bushing
002026491
110924PC740 Pipe Bushing
002783167
Page:

Engine, Aircraft, F100-pw-100 (f-15a/b/c/d)

Picture of F100-pw-100 (f-15a/b/c/d)  Aircraft Engine

The Pratt & Whitney F119 (company designation PW5000) is an afterburning turbofan engine developed by Pratt & Whitney for the Lockheed Martin F-22 Raptor advanced tactical fighter.

The engine delivers thrust in the 35,000 lbf (160 kN) class, and is designed for supersonic flight without the use of afterburner (supercruise). Delivering almost 22% more thrust with 40% fewer parts than conventional, fourth-generation military aircraft engine models, the F119 allows sustained supercruise speeds of up to Mach 1.8. The F119's nozzles incorporate 2D thrust vectoring technology. These nozzles direct the engine thrust ±20° in the pitch axis to give the F-22 enhanced maneuverability.

The F119 derivative, the F135, produces 40,000 lbf (180 kN) of thrust for the Lockheed Martin F-35 Lightning II.

The F119 resulted from the Joint Advanced Fighter Engine (JAFE) program in the early 1980s aimed at supplying the powerplant for the Air Force's Advanced Tactical Fighter (ATF). Detailed design of Pratt & Whitney's submission, designated internally as PW5000, began when the JAFE request for proposals (RFP) was released in May 1983. Advances in engine technology, such as those from the Integrated High Performance Turbine Engine Technology (IHPTET) program, allowed the design to do more work with fewer stages, with the PW5000 having only 6 compressor stages compared to the F100's 10 compressor stages. The high pressure and low pressure turbines were single stage and counter-rotating, thus shortening the engine and saving weight. The fan and compressor stages were to use integrally bladed rotors (IBR) to reduce weight and cost and improve performance. The combustor, designated Floatwall, eliminates welds to mitigate crack growth due to thermal cycling. This technology allows the engine to achieve very high core temperatures to meet the requirement for high specific thrust for supercruising. The original RFP called for maximum thrust in the 30,000 lbf class.

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