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(Top) 1 Variants 2 Applications 3 Specifications (T64-GE-100) 3.1 General characteristics 3.2 Components 3.3 Performance 4 See also 5 Notes 6 References 7 External links

General Electric T64

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T64

Cutaway of a T64-IHI-10E (inturboprop configuration)
Type	Turboshaft
National origin	United States
Manufacturer	GE Aviation
First run	(T64-GE-2) March 1959
Major applications	Lockheed AH-56 Cheyenne Alenia G.222 de Havilland Canada DHC-5 Buffalo Sikorsky CH-53 Sea Stallion Sikorsky CH-53E Super Stallion

The General Electric T64 is a free-turbine turboshaft engine that was originally developed for use on helicopters, but which was later used on fixed-wing aircraft as well. General Electric introduced the engine in 1964. The original engine design included technical innovations such as corrosion resistant and high-temperature coatings.^[1] The engine features a high overall pressure ratio, yielding a low specific fuel consumption for its time.^[2] Although the compressor is all-axial, like the earlier General Electric T58, the power turbine shaft is coaxial with the HP shaft and delivers power to the front of the engine, not rearwards. Fourteen compressor stages are required to deliver the required overall pressure ratio. Compressor handling is facilitated by 4 rows of variable stators. Unlike the T58, the power turbine has 2 stages.

Later versions of the engine produce from 3,925 to 4,750 shp (2,927 to 3,542 kW).^[3]

The engine was designed to accommodate different gearboxes or shaft drives, for helicopter or turboprop fixed-wing applications. The engine could be operated continuously at angles between 100 degrees upward and 45 degrees downward for STOL or helicopter applications.^[4]

Variants[edit]

T64-GE-7 installed on Sikorsky CH-53G helicopter

Data from: Vectorsite;Sikorsky Giant Helicopters^[5]

T64-GE-1

3,080 hp (2,300 kW)

T64-GE-2

Turbo-shaft: 2,810 hp (2,100 kW) at 5,200 rpm output^[6]

T64-GE-3

T64-GE-4

Turbo-prop, reduction gearbox below centre-line, airscrew brake and bolt-on control unit: 2,850 hp (2,130 kW) at 1,160 propeller rpm.^[6]

YT64-GE-6

2,850 hp (2,130 kW) used for Hughes XV-9 hot-cycle hot cycle rotor drive research helicopter.

T64-GE-6

Turbo-shaft: 2,850 hp (2,130 kW) at 13,600 engine rpm.^[6]

T64-GE-7

3,925 hp (2,927 kW)

T64-GE-7A

3,936 hp (2,935 kW)

T64-GE-8

Turbo-prop, reduction gearbox above centerline, airscrew brake and bolt-on control unit: 2,850 hp (2,130 kW) at 1,160 propeller rpm.^[6]

T64-GE-10

2,970 hp (2,210 kW)

T64-GE-16

3,485 hp (2,599 kW)

T64-GE-100

4,330 hp (3,230 kW)

T64-GE-412

3,695 hp (2,755 kW)

T64-GE-413

3,925 hp (2,927 kW)

T64-GE-413A

3,936 hp (2,935 kW)

T64-GE-415

4,380 hp (3,270 kW)

T64-GE-416

4,380 hp (3,270 kW) - three on Sikorsky CH-53E Super Stallion^[7]

T64-GE-419

4,750 hp (3,540 kW) engine to power the Bell V-280 Valor demonstrator tiltrotor aircraft^[8]

T64-GE-423

3,925 hp (2,927 kW)

T64-BS-12

T63-BS-16

T64-P4D

Turboprop 3,400 hp (2,500 kW)

CT64-820-1

2,850 hp (2,130 kW)

CT64-820-2

CT64-820-3

3,130 hp (2,330 kW)

CT64-820-4

3,133 hp (2,336 kW)

T64/P4D

3,400 hp (2,500 kW)^[9]

Ishikawajima-Harima T64-IHI-10

For Kawasaki P-2J and Shin Meiwa PS-X

Applications[edit]

Aeritalia G.222

de Havilland Canada DHC-5 Buffalo

Lockheed AH-56 Cheyenne

Sikorsky CH-53 Sea Stallion

Sikorsky CH-53E Super Stallion

Sikorsky HH-53/MH-53

Specifications (T64-GE-100)[edit]

Data from Gas Turbine Engines^[10]

General characteristics

Type: Turboshaft engine
Length: 79 in (2,007 mm)
Diameter: 20 in (508 mm)
Dry weight: 720 lb (327 kg)

Components

Compressor: Axial, 14 stage HP compressor
Combustors: Annular
Turbine: Axial, 2 stage HP turbine, 2 stage PT turbine
Fuel type: Aviation kerosene
Oil system: Pressure spray / splash

Performance

Maximum power output: 4,330 hp (3,228.88 kW)
Overall pressure ratio: 14.9:1
Turbine inlet temperature: 1,180 °F (638 °C)(-1), 1,325 °F (718 °C)(-413), 1,410 °F (770 °C)(-415)^[11]
Specific fuel consumption: 0.48 lb/(hp⋅h) (0.29 kg/kWh)
Power-to-weight ratio: 6.014 hp/lb (9.887 kW/kg)

Notes[edit]

^ GE T64 page, GlobalSecurity.org, accessed October 29, 2007.

^ Gunston, W.T. (January 13, 1961). "T64: Design philosophy behind GE's new shaft turbine". Flight. pp. 63–64. Archived from the original on January 11, 2019.

^ T64 turboshaft page Archived 2011-06-20 at the Wayback Machine, GE Aviation, accessed October 29, 2007.

^ "General Electric T-64". Newsreel. Flying. May 1962. p. 68.

^ "Sikorsky Giant Helicopters: S-64, S-65, & S-80". Vectorsite. 1 March 2008. Retrieved 5 January 2018.

^ ^a ^b ^c ^d Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.

^ "About the GE T64 Archived 2014-04-13 at the Wayback Machine" BGA-aeroweb, May 17, 2012. Accessed: April 10, 2014.

^ Tomkins, Richard (October 15, 2014). "GE Aviation supplying engines for V-280 demo aircraft". United Press International.

^ John W.R. Taylor, ed. (1988). Jane's All the World's Aircraft 1988-89. London: Jane's Information Group. ISBN 0-7106-0867-5.

^ Gas Turbine Engines. Aviation Week & Space Technology Source Book 2009. p. 118.

^ Leyes, Richard A.; Fleming, William A. (1999). The history of North American small gas turbine aircraft engines. pp. 293–310. ISBN 9781563473326.

References[edit]

General Electric (July 16, 1986). E13EA. Federal Aviation Administration (FAA) (Report). Type Certificate Data Sheet (12th ed.).

Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.

External links[edit]

Wikimedia Commons has media related to General Electric T64.

GE Aviation T64 page
GE Aviation Receives AHS Supplier Excellence Award (for T64 team) Archived 2011-07-22 at the Wayback Machine

v t e GE Aircraft Engines/GE Aviation/GE Aerospace aircraft engines
Turbojets	CJ610 CJ805 GE1 GE4/J5 I-A J31 J33 J35 J47 J73 J79 J85 J87 YJ93 J97 YJ101
Turbofans	Affinity CF6 CF34 CF700 CFE738† CFM56† CJ805-23 GE90 GE9X GEnx GP7000† HF120† LEAP† Passport F101 F108† F110 F118 YF120 F136† F404/F412 F414 RM12† RM16 TF34 TF39 XA100 XA102
Turboprops and turboshafts	Catalyst CT7 CT58 CT64 GE27 GE38 H-Series T31 T58 T64 T407 T408 T700 T901
Aeroderivative gas turbine engines	LM500 LM1500 LM1600 LM2500 LM6000 LM9000 LMS100
Propfans	GE36 RISE†
† Joint development aeroengines

v t e 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 J51 J52 J53 J54 J55 J56 J57 J58 J59 J60 J61 J63 J65 J67 J69 J71 J73 J75 J79 J81 J83 J85 J87 J89 J91 YJ93 J95 J97 J99 J100 YJ101 J102 J400 J401 J402 J403 J700
Turboprops/ Turboshafts	T30 T31 T33 T34 T35 T36 T37 T38 T39 T40 T41 T42 T43 T44 T45 T46 T47 T48 T49 T50 T51 T52 T53 T54 T55 T56 (variants) T57 T58 T60 T61 T62 T63 T64 T65 T66 T67 T68 T69 T70 T71 T72 T73 T74 T76 T78 T80 T100 T101 T400 T405 T406 T407 T408 T700 T701 T702 T703 T706 T708 LHTEC T800 APW T800 T900 T901
Turbofans	TF30 TF31 TF32 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 F400 F401 F402 F404 F405 F408 F412 F414 F415
Adaptive cycle engines	XA100 XA101 XA102 XA103

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v t e 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 L M 118 A L P 119 C/F E L T Y 120 121 122 123 124 125 126 127¹ 128 129 130 131 132 A B 133 134¹ 135 136¹ 137¹ 138 139 140 141¹ 142 143–197¹ 198 199 B C D Y
200–299	200 201 A/L B/W E 202 203¹ 204 205 206 207¹ 208 209¹ 210 211¹ 212 213 214 215¹ 216 217 218 219¹ 220 221 222 A G 223¹ 224 225¹ 226 227–238¹ 239 240–278¹ 279 280–298¹ 299
300–399	300 301¹ 302 303 304¹ 305¹ 306 A/L B 307 308 309 310¹ 311¹ 312¹ 313¹ 314 315 A-1 A-2 316 317 318¹ 319 320¹ 321 322¹ 323 324 L M/N 325 326 327 E 328 E 329 F 330¹ 331¹ 332¹ 333¹ 334¹ 335 336 337 338–379¹ 380 A/B/E/F/N P 381–397¹ 398 399 A B
400–499	400 B/C/N E G/H M 401 402 403¹ 404 405 B C D 406¹ 407 408¹ 409¹ 410 E L 411 E L 412 413 414 L M 415 416 L M (I) M (II) P Q 417 418 L M 419¹ 420 L/W 421¹ 422 423 424 425 426 L M 427 L M 428 A L 429 430 431 G (I) G (II) 432 433 434 435 A L 436 437 438 439 440 441 A D L 442 443 444¹ 445 L M 446 447 448¹ 449¹ 450 451 D L 452 453 454¹ 455 456 457¹ 458 459 460 L 461 462 463 464 465 466 467 468 469 470 471 L (I) L (II) 472 473 474 L N 475¹ 476 E 477 478 A T 479¹ 480 481 L 482 E L M/Z 483 484 L M N 485 L Z 486 487 488 489 490 L M 491¹ 492 493 494 495 L (I) L (II) 496 497 A L (I) L 498 A C D E L 499 A C D
500–599	500 501–519¹ 520 521–529¹ 530 531–541¹ 542 543–549¹ 550 A E 551–559¹ 560 A F 561–569¹ 570 571–579¹ 580 A E 581–589¹ 590 591 592 593–599¹
600–699	600 601 A L 602 A L 603 A L 604 605 606 607 608¹ 609 610¹ 611¹ 612¹ 613¹ 614 615¹ 616 617¹ 618 619¹ 620 621 A/B (I) B (II) 622 623 624 625 626¹ 627 628¹ 629¹ 630¹ 631¹ 632 633 634 A B 635 636¹ 637¹ 638 639 640 641 642 643 644¹ 645¹ 646¹ 647¹ 648 A D P 649 A B C D E F L P 650 651 652 653¹ 654¹ 655 A (I) A (II) P 656 657¹ 658¹ 659¹ 660 661 662¹ 663¹ 664 665 A (I) A (II) 666 A C/P 667 668 669¹ 670 671¹ 672 A M/P 673¹ 674 675 676¹ 677¹ 678¹ 679 680 681 D E 682¹ 683 A J V 684¹ 685 686 687 J P 688¹ 689¹ 690 691 C X 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 736 737¹ 738¹ 739¹ 740¹ 741 742 743 744¹ 745 746–753¹ 754 755–799¹
800–899	800¹ 801¹ 802 L (I) L (II) 803¹ 804¹ 805¹ 806 807 808–816¹ 817 818¹ 819¹ 820¹ 821¹ 822¹ 823 824–831¹ 832 833¹ 834 835–845¹ 846 847–899¹
900–999	900–951¹ 952 853¹ 854¹ 855¹ 956 957–967¹ 968
¹ Unknown or not assigned