Pratt & Whitney F100

F100
	F100 for an F-15 Eagle being tested
Type	Turbofan
National origin	United States
Manufacturer	Pratt & Whitney
First run	1970s
Major applications	F-15 Eagle ; F-15E Strike Eagle ; F-16 Fighting Falcon ; Northrop Grumman X-47B
Developed into	Pratt & Whitney PW1120

The Pratt & Whitney F100 (company designation JTF22^[1]) is an afterburning turbofan engine manufactured by Pratt & Whitney that powers the F-15 Eagle and F-16 Fighting Falcon.

Development[]

Afterburner - concentric ring structure inside the exhaust

In 1967, the United States Navy and United States Air Force issued a joint engine Request for Proposals (RFP) for the F-14 Tomcat and the FX. (The FX became the parallel fighter design competition that led to the F-15 Eagle in 1970.)

This engine program was called the IEDP (Initial Engine Development Program). It was funded and managed out of the Aeronautical Systems Division (ASD) at Wright Patterson AFB. Under ASD, a Systems Project Office Cadre was assigned to manage both the FX Aircraft and Engine definition phase. The Turbine Engine Division of the Air Force Propulsion Laboratory was employed in a support role to assist ASD Systems Engineering in evaluations of technical risks. Later upon selection of the F-15 the ASD engineering cadre became the F-15 Systems Project Office.

Adjustable exhaust nozzle contracted

The IEDP was created to be a competitive engine design/demonstration phase followed with a down select to one winning engine design and development program. General Electric and Pratt Whitney were placed on contract for an approximately 18-month program with goals to improve thrust and reduce weight to achieve a thrust-to-weight ratio of 8. At the end of the IEDP, GE and PW submitted proposals for their engine candidates for the Aircraft that had been selected in the FX Competition. That Fighter was the McDonnell F-15 Fighter. The engine was designated the Pratt Whitney F-100 engine. The Air Force would award Pratt & Whitney a contract in 1970 to develop and produce F100-PW-100 (USAF) and F401-PW-400 (USN) engines. The Navy would use the engine in the failed XFV-12 project but would cut back and later cancel its order, choosing to continue to use the Pratt & Whitney TF30 engine from the F-111 in its F-14.^[2]

Variants[]

F100-PW-100[]

F100-PW-100 on display at the Virginia Air and Space Center

The F100-100 first flew in an F-15 Eagle in 1972 with a maximum continuous power rating of 12,410 lbf (55.2 kN) and afterburning thrust of 23,930 lbf (106.4 kN) with 5-minute limit. Due to the advanced nature of engine and aircraft, numerous problems were encountered in its early days of service including high wear, stalling^[3] and "hard" afterburner starts. These "hard" starts could be caused by failure of the afterburner to start or by extinguishing after start, in either case the large jets of jet fuel were lit by the engine exhaust resulting in high pressure waves causing the engine to stall. Early problems were solved in the F100-PW-220, and the engine is still in the USAF fleet to this day.

F100-PW-200[]

The F-16 Fighting Falcon entered service with the F100-200, with only slight differences from the -100. Seeking a way to drive unit costs down, the USAF implemented the Alternative Fighter Engine (AFE) program in 1984, under which the engine contract would be awarded through competition. The F-16C/D Block 30/32s were the first to be built with the common engine bay, able to accept the existing engine or the General Electric F110.

F100-PW-220/220E[]

Due to the unsatisfactory reliability, maintenance costs, and service life of the F100-PW-100/200, Pratt & Whitney was eventually pressured into upgrading the engine to address these issues. The resulting engine, designated F100-PW-220, almost eliminates stall-stagnations and augmenter instability as well as doubling time between depot overhauls. Reliability and maintenance costs were also drastically improved, and the engine incorporates a digital electronic engine control (DEEC). The F100-PW-220 was introduced in 1986 and could be installed on either an F-15 or F-16.^[4] A non-afterburning variant, the F100-PW-220U powers the Northrop Grumman X-47B UCAV. The "E" abbreviation from 220E is for equivalent. The abbreviation is given to engines which have been upgraded from series 100 or 200 to 220, thus becoming equivalent to 220 specifications.

F100-PW-229[]

The first -229 was flown in 1989 and has a thrust of 17,800 lbf (79 kN) (dry thrust) and 29,160 lbf (129.7 kN) with afterburner. It currently powers late model F-16s and F-15Es. Using technology developed from the F119 and F135 engine programs for the F-22 Raptor and F-35 Lightning II, the current production F100-PW-229 EEP (Engine Enhancement Package) incorporates modern turbine materials, cooling management techniques, compressor aerodynamics, split cases (top and bottom) and electronic controls.^[5] Deliveries of the -229EEP began in 2009.

Applications[]

An F401 engine for Rockwell XFV-12 prototype supersonic VTOL fighter

F100

General Dynamics F-16 Fighting Falcon
McDonnell Douglas F-15 Eagle
McDonnell Douglas F-15E Strike Eagle
Northrop Grumman X-47B
Vought YA-7F

F401

Convair Model 200
Grumman F-14B Tomcat (planned; test aircraft only)
Rockwell XFV-12
Vought Model 1600 (proposed)

Specifications (F100)[]

F100-PW-220[]

Data from DTIC,^[4] Florida International University,^[6] National Museum of the U.S. Air Force^[7]

General characteristics

Type: Afterburning turbofan
Length: 191 inches (490 cm)
Diameter: 34.8 inches (88 cm) inlet, 46.5 inches (118 cm) maximum external
Dry weight: 3,234 pounds (1,467 kg)

Components

Compressor: Dual Spool Axial compressor
Bypass ratio: 0.71:1
Combustors: annular

Performance

Maximum thrust:
- 14,590 pounds-force (64.9 kN) military thrust,
- 23,770 pounds-force (105.7 kN) with afterburner
Overall pressure ratio: 25:1
Specific fuel consumption: Military thrust: (0.73 lb/(lbf·h))
Thrust-to-weight ratio: 7.4:1

F100-PW-229[]

Data from Pratt & Whitney^[8]

General characteristics

Type: Afterburning turbofan
Length: 191 inches (490 cm)
Diameter: 34.8 inches (88 cm) inlet, 46.5 inches (118 cm) maximum external
Dry weight: 3,829 pounds (1,737 kg)

Components

Compressor: Dual Spool Axial compressor with 3 fan and 10 compressor stages
Bypass ratio: 0.36:1
Combustors: annular
Turbine: 2 low-pressure and 2 high-pressure stages

Performance

Maximum thrust:
- 17,800 pounds-force (79 kN) military thrust
- 29,160 pounds-force (129.7 kN) with afterburner
Overall pressure ratio: 32:1
Turbine inlet temperature: 2,460 °F (1,350 °C)^[9]
Specific fuel consumption: Military thrust: 0.76 lb/(lbf·h) (77.5 kg/(kN·h)) Full afterburner: 1.94 lb/(lbf·h) (197.8 kg/(kN·h))
Thrust-to-weight ratio: 7.8:1

References[]

^ "Designations Of U.S. Military Aero Engines". www.designation-systems.net. Retrieved 17 April 2018.
^ Davies, Steve. Combat Legend, F-15 Eagle and Strike Eagle. London: Airlife Publishing, Ltd., 2002. ISBN 1-84037-377-6.
^ Fernandez 1983, pp. 241–245, 251–254
^ Jump up to: ^a ^b "The Development of the F100-PW-220 and F110-GE-100 Engines: A Case Study of Risk Assessment and Risk Management" (PDF). dtic.mil. Retrieved 17 April 2018.
^ "F100-PW-229 Engine Enhancement Package brochure" (PDF). Archived from the original (PDF) on 2014-01-12. Retrieved 2014-01-12.
^ http://www.allstar.fiu.edu/aero/P&WEngines02.html
^ "Pratt & Whitney F100-PW-220". National Museum of the United States Air Force. May 28, 2015.
^ P&W F100 product page. Archived August 15, 2010, at the Wayback Machine
^ Clancy, Tom (2007). Fighter Wing: A Guided Tour of an Air Force Combat Wing. ISBN 9780425217023.

Bibliography[]

Fernandez, Ronald (1983), Excess Profits: The Rise of United Technologies, Boston: Addison-Wesley, ISBN 9780201104844.

External links[]

[1] "Designations Of U.S. Military Aero Engines". www.designation-systems.net. Retrieved 17 April 2018.

[Davies-2] Davies, Steve. Combat Legend, F-15 Eagle and Strike Eagle. London: Airlife Publishing, Ltd., 2002. ISBN 1-84037-377-6.

[Fernandez1983pp241-245,251-254-3] Fernandez 1983, pp. 241–245, 251–254

[dtic.mil-4] Jump up to: ^a ^b "The Development of the F100-PW-220 and F110-GE-100 Engines: A Case Study of Risk Assessment and Risk Management" (PDF). dtic.mil. Retrieved 17 April 2018.

[5] "F100-PW-229 Engine Enhancement Package brochure" (PDF). Archived from the original (PDF) on 2014-01-12. Retrieved 2014-01-12.

[6] ttp://www.allstar.fiu.edu/aero/P&WEngines02.html

[7] "Pratt & Whitney F100-PW-220". National Museum of the United States Air Force. May 28, 2015.

[8] P&W F100 product page. Archived August 15, 2010, at the Wayback Machine

[9] Clancy, Tom (2007). Fighter Wing: A Guided Tour of an Air Force Combat Wing. ISBN 9780425217023.

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show v t Pratt & Whitney aircraft engines
Radial engines	R-985 R-1340 R-1535 R-1690 R-1830 R-1860 R-2000 R-2060 R-2180-A R-2180-E R-2800 R-4360 Double Wasp Hornet (A) Hornet B Twin Hornet Twin Wasp (R-1830) Twin Wasp (R-2000) Twin Wasp E Twin Wasp Junior Wasp series Wasp Wasp Junior Wasp Major Yellow Jacket
H piston engines	X-1800/XH-2600 XH-3130 (XH-3730)
Free-piston gas turbines	PT1
Turbojets	JT3C JT4A JT6 JT7 JT8A JT11 JT12 J42 J48 J52 J57 J58 J60 J75
Turbofans	GP7000† JT3D JT4D JT8D JT9D JTF10A JT10D JTF22 PW1000G PW1120 PW2000 PW4000 PW5000 PW6000 SuperFan† V2500† F100 F105 F117 F119 F135 F401 TF30 TF33 XA101 RM8
Turboprops/Turboshafts	APW34† JFTD12 PT2 PT5 T34 XT57 T73 T800-APW† T900†
Propfans	578-DX†
Rocket engines	RL10
Aeroderivative gas turbine engines	GG4/FT4
Subsidiaries	Pratt & Whitney Canada Pratt & Whitney Rocketdyne
Key people	Leonard S. Hobbs George J. Mead Frederick Rentschler Richard "Dick" Soderberg
† Joint development aeroengines See also: Pratt & Whitney Canada aeroengines

show v t United States military gas turbine aircraft engine designation system
Turbojets	J30 J31 J32 J33 J34 J35 J36 J37 XJ38 J39 J40 XJ41 J42 J43 J44 J45 J46 J47 J48 XJ49 J52 J54 J55 J57 J58 J60 J65 J67 J69 J71 J73 J75 J79 J81 J83 J85 J87 YJ93 J97 J100 YJ101 J102 J400 J402 J403 J700
Turboprops/ Turboshafts	T31 T33 T34 T35 T36 T37 T38 T39 T40 T41 T44 T46 T47 T49 T50 T51 T53 T54 T55 T56 (variants) T57 T58 T60 T61 T62 T63 T64 T65 T66 T67 T72 T73 T74 T76 T101 T400 T406 T407 T408 T700 T701 T702 T703 T706 LHTEC T800 APW T800 T900 T901
Turbofans	TF30 TF33 TF34 TF35 TF37 TF39 TF41 F100 F101 F102 F103 F104 F105 F106 F107 F108 F109 F110 F112 F113 F117 F118 F119 YF120 F121 F122 F124 F125 F126 F127 F128 F129 F130 F135 F136 F137 F138 F401 F402 F404 F405 F408 F412 F414
Adaptive cycle engines	XA100 XA101

show v t United States Air Force system numbers
100–199	100 101 P 102 103 104 105 106¹ 107 A-1 A-2 108¹ 109¹ 110 111¹ 112 113¹ 114¹ 115¹ 116¹ 117 M 118 A 119 C/F E T Y 120 121 122 123 124 125 127¹ 129 131 132 133 134¹ 136¹ 137¹ 138 139 140 141¹ 142 143–197¹ 199 B C D
200–299	200 201 A/L B/W E 202 203¹ 204 205 206 207¹ 208 209¹ 210 211¹ 213 214 215¹ 216 217 218 219¹ 220 221 222 A 223¹ 224 225¹ 226 227–238¹ 239 240–278¹ 279 280–298¹
300–399	300 301¹ 302 303 304¹ 305¹ 306 A/L B 307 308 309 310¹ 311¹ 312¹ 313¹ 314 315 A-1 A-2 316 318¹ 319 320¹ 321 322¹ 324 L M/N 326 327 E 328 E 329 F 330¹ 331¹ 332¹ 333¹ 334¹ 335 336 337 338–379¹ 380 A/B/E/F/N P 381–397¹ 399
400–499	400 B/C/N E G/H M 401 402 403¹ 405 406¹ 408¹ 409¹ 410 E 411 E L 413 414 416 L M (I) 418 419¹ 420 L/W 421¹ 422 423 424 425 426 L 427 L 428 L 429 431 434 435 L 436 441 A L 442 443 444¹ 445 446 447 448¹ 449¹ 450 451 L 452 453 454¹ 457¹ 460 L 462 463 464 465 468 471 L (I) L (II) 474 L N 475¹ 476 E 477 478 A 479¹ 481 L 482 E M/Z 484 485 Z 487 488 490 491¹ 493 494 495 496 497 L 498 C E L 499
500–599	501–519¹ 521–529¹ 531–541¹ 543–549¹ 550 551–559¹ 560 561–569¹ 571–579¹ 580 581–589¹ 591 593–599¹
600–699	601 A 602 A 603 A 605 606 607 608¹ 609 610¹ 611¹ 612¹ 613¹ 615¹ 616 617¹ 619¹ 620 621 A/B (I) 622 624 626¹ 628¹ 629¹ 630¹ 631¹ 634 A B 636¹ 637¹ 638 641 644¹ 645¹ 646¹ 647¹ 648 A P 649 P 653¹ 654¹ 655 656 657¹ 658¹ 659¹ 662¹ 663¹ 665 666 669¹ 671¹ 672 673¹ 676¹ 677¹ 678¹ 681 682¹ 683 A V 684¹ 687 P 688¹ 689¹ 691 C Z 692¹ 693 694¹ 695 A B C L N P Q R S (I) S (II) 696¹ 697¹ 698¹ 699¹
700–799	700–735¹ 737¹ 738¹ 739¹ 740¹ 742 743 744¹ 745 746–753¹ 755–799¹
800–899	800¹ 801¹ 802 803¹ 804¹ 805¹ 807 808–816¹ 818¹ 819¹ 820¹ 821¹ 822¹ 824–831¹ 832 833¹ 834 835–845¹ 847–899¹
900–999	900–951¹ 952 853¹ 854¹ 855¹ 956 957–967¹
¹ Unknown or not assigned

Pratt & Whitney F100

Contents

Development[]

Variants[]

F100-PW-100[]

F100-PW-200[]

F100-PW-220/220E[]

F100-PW-229[]

Applications[]

Specifications (F100)[]

F100-PW-220[]

General characteristics

Components

Performance

F100-PW-229[]

General characteristics

Components

Performance

See also[]

References[]

Bibliography[]

External links[]