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

(Page 5) End item NSN parts page 5 of 38
Part Number
NSN
NIIN
015-90010-58 Pipe Bushing
002783167
015-TH1257 O-ring
007651948
01521 Electrical Power Cable
005481243
018-C-69 O-ring
002483848
0187-3-4X1-2 Pipe Bushing
002783167
019076 Nonmetallic Hose
002893306
020-108N Waveguide Flange Cover
009541625
02042-85 Electrical Power Cable
005481243
02055990 Fluid Filter Element
014236207
021-00039 Liquid Sight Indicator
009296667
0221 Electrical Box Connector
005783666
024-7866 O-ring
002500236
0240-D-010-BHHC Fluid Filter Element
014236207
0245604-7 O-ring
009425120
0245604-70 O-ring
009425120
025-0484-000 Dust And Moi Protective Cap-plug
001712436
02637 O-ring
002917384
02654 O-ring
004359355
026L601/Y-302 Liquid Sight Indicator
009296667
028-07407K O-ring
001675121
Page: 5 ...

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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