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

(Page 6) End item NSN parts page 6 of 38
Part Number
NSN
NIIN
0296619-1 Pipe Elbow
001377875
03-0005-220 Film Fixed Resistor
002431450
03-0804-A928 Knitted Wire Mesh
000053272
03-825-04 Self-aligning Plain Bearing
010069515
030-9036-000 Electrical Contact
011343598
030-C-69 O-ring
008412366
0300-12 S Electrical Insulation Sleeving
007564381
0303-6-6 Tube Nipple
007816089
031-1123-016 Electrical Contact
001973621
031640 O-ring
002483848
033514-0000 Electrical Conduit Locknut
006427261
033777-0003 Electrical Conduit Bushing
005782859
034-C-69 O-ring
004359355
038072-00-40 Fluid Filter Element
002033593
038072-40 Fluid Filter Element
002033593
038072-44 Fluid Filter Element
002033593
038498-31 Fluid Filter Element
010334594
03L3-8-8C Boss Nipple
000677564
000039157
0407-128 Machine Screw
009254774
Page: 6 ...

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.

Compare Now »
Clear | Hide