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

(Page 7) End item NSN parts page 7 of 38
Part Number
NSN
NIIN
0408743 Hose Clamp
011919701
0419-503 Hexagon Head Cap Screw
006322777
041K60900 Machine Screw
005147506
042023-1 Electrical Contact
002852987
0431537 Pipe To Tube Straight Adapter
002891930
044948 Retaining Ring
002816623
0457-128 Machine Screw
009254774
04603 Electrical Box Connector
001008716
05007-0038 Machine Screw
009254774
0510-0082 Retaining Ring
002002637
05592A Tube Coupling Nut
009028990
058166-0001 Nonmetallic Hose
002423135
060115B Tube-hose Fit Compression Sleeve
011937390
06057300 Tube Coupling Nut
003148366
06110-0604 Pipe Bushing
002026491
06247 Cartridge Fuse
005536957
0625388 Electrical Conduit Locknut
007148031
063T-4-4 Tube Tee
006185382
0660-D-005-BHHC Fluid Filter Element
014236198
06932D-632 Tube To Hose Straight Adapter
010946830
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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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