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

(Page 16) End item NSN parts page 16 of 38
Part Number
NSN
NIIN
10117063 O-ring
001675123
10117097 O-ring
005373929
10117099 O-ring
005493628
10117135 O-ring
010050509
10117271 Dust And Moi Protective Cap-plug
001712436
10117300 Dust And Moisture Protective Cap
002082195
10117348 Dust And Moisture Protective Cap
003649560
10117377 Dust And Moisture Protective Cap
004935835
10117462 Dust And Moistur Protective Plug
008170912
10117579 Loop Clamp
010575505
10119447 Preformed Packing
001799377
10119522 Packing Retainer
007203652
10119537 Packing Retainer
008204142
10119541 Packing Retainer
008334210
1012-8-4S Pipe To Tube Straight Adapter
004418700
10120316 Film Fixed Resistor
001374824
10120357 Film Fixed Resistor
001392163
10120660 Film Fixed Resistor
002850686
10121403 Recessed Washer
004767366
10121404 Recessed Washer
004767367
Page: 16 ...

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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