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

(Page 8) End item NSN parts page 8 of 38
Part Number
NSN
NIIN
0698-4262 Film Fixed Resistor
002431450
0698-8641 Film Fixed Resistor
002850686
069D12-612 Tube To Hose Straight Adapter
000755684
06P228822-01 Voltage Sensitive Resistor
002559504
07-13-01 Nonmetallic Tubing
002692189
07-59F2 Pipe To Tube Straight Adapter
002891930
070102-3/8X3/8SS Pipe To Tube Straight Adapter
005117989
0701969 Socket Head Cap Screw
009789396
071005 Flat Washer
013529593
0716-MM5 Pipe Bushing
002783167
0716-MM5-J10 Pipe Bushing
002783167
0740671 Socket Head Cap Screw
009887607
0740682 Socket Head Cap Screw
009836660
0740710 Cotter Pin
001850037
0740783 Hexagon Head Cap Screw
007175460
075578 Power Supply
011014048
0757-0430 Film Fixed Resistor
002431450
0757-0932 Film Fixed Resistor
002431450
076-005783-003 Dust And Moistur Protective Plug
005306818
076-005783-008 Dust And Moisture Protective Cap
004947597
Page: 8 ...

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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