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

(Page 10) End item NSN parts page 10 of 38
Part Number
NSN
NIIN
0N410178-1 Electrical Clip
012505117
0N505509 Clamping Catch
000145987
0R0-0232-405 O-ring
002519364
1-0133 Connector Adapter
001054642
1-100S Electrical Conduit Locknut
007148031
1-2FNTX-SS Tube Cap
010442446
1-3062-1 Packing Retainer
007203652
1-40D Metallic Tube
002033171
1-42-812-5 Retaining Ring
002816623
1-4CRSS Pipe Elbow
001377875
1-4D1AX5-8LG Headless Straight Pin
009265761
1-4DIAX5-8LG Headless Straight Pin
009265761
1-75 Electrical Conduit Locknut
006427261
1-801137-1 Electr Receptacle Connector Body
010137223
1-802109-1 Electr Receptacle Connector Body
000329561
1-802115-1 Electr Receptacle Connector Body
000329560
1-802137-1 Electr Receptacle Connector Body
000329566
1/2 351 Ball Valve
004171120
1/2-13X2-1/2 IN. Hexagon Head Cap Screw
006166375
1/211-1100TT Ball Valve
004171120
Page: 10 ...

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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