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

(Page 28) End item NSN parts page 28 of 38
Part Number
NSN
NIIN
11-229 O-ring
002913273
11-50 Electrical Box Connector
005783666
110-3/8X1/4 Pipe Bushing
002026491
110-37 Pipe Tee
007192708
110-5781 Pipe Nipple
001961498
110-5801 Pipe Nipple
001961496
110-B-12X08 Pipe Bushing
002783167
110005 Test Lead Set
010135137
1100S750-0P0RM1PCT Induct Wire Wound Fixed Resistor
011851941
110126-5 Dust And Moistur Protective Plug
002923292
1102 Conduit Chase Nipple
002808558
11024020 Ball Valve
004171120
11024885 Electrical Box Connector
005783666
1102DC Conduit Chase Nipple
002808558
1103 Electrical Conduit Bushing
001521094
11060A Pipe To Tube Straight Adapter
002784322
110811 Shipping And Storage Drum
002929783
11089 Pipe Bushing
002026491
110924PC740 Pipe Bushing
002783167
110930PC740 Pipe Bushing
002783167
Page: 28 ...

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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