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

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Part Number
NSN
NIIN
06932D-632 Tube To Hose Straight Adapter
010946830
069D12-612 Tube To Hose Straight Adapter
000755684
1000211-3232 Tube To Hose Straight Adapter
010946830
13208E6819-6 Tube To Hose Straight Adapter
003746954
136-1000-16D Tube To Hose Straight Adapter
005856212
16C16FJSR Tube To Hose Straight Adapter
003746954
20620-32-32-32 Tube To Hose Straight Adapter
010946830
20622-12-12 Tube To Hose Straight Adapter
000755684
20622-32-32 Tube To Hose Straight Adapter
010946830
23-411-12 Tube To Hose Straight Adapter
000755684
319-12 Tube To Hose Straight Adapter
000755684
319-12S Tube To Hose Straight Adapter
000755684
411-12S Tube To Hose Straight Adapter
000755684
411-32S Tube To Hose Straight Adapter
010946830
4721-16S Tube To Hose Straight Adapter
003746954
516-16C Tube To Hose Straight Adapter
005856212
63357-12-12 Tube To Hose Straight Adapter
000755684
74649-33X4PC14 Tube To Hose Straight Adapter
000755684
816-16D Tube To Hose Straight Adapter
005856212
9125145 Tube To Hose Straight Adapter
003746954
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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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