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

(Page 4) End item NSN parts page 4 of 38
Part Number
NSN
NIIN
010-11647 O-ring
003431035
010-7866 O-ring
002638032
0101-2211 Film Fixed Resistor
002431450
010116-008 Retaining Ring
008046896
0102-6-4B Pipe Bushing
002026491
0103-12-12C Pipe To Tube Straight Adapter
007960496
0103-8-6C Pipe To Tube Straight Adapter
000798814
0104-02-12 O-ring
002500221
010487 Filler Opening Cap
010416607
01055 O-ring
002483848
0119928 Pipe Bushing
002026491
01253074 Fluid Filter Element
014236207
013-0020-00 Test Adapter
008872395
013-0056-00 Test Adapter
008872395
013-020 Test Adapter
008872395
013-056 Test Adapter
008872395
013-13029-1 Thyristor Semiconductor Device
000089784
014183-0000 Circuit Breaker
010420109
015-11647 O-ring
007651948
015-1393-70 O-ring
007651948
Page: 4 ...

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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