Honeywell's T55-GA-714A turboshaft engine on a CH-47 Chinook
Type Turboshaft
National origin United States
Manufacturer Lycoming Engines
Honeywell Aerospace
First run April 1955
Major applications Bell 309 KingCobra
Boeing CH-47 Chinook
Piper PA-48 Enforcer
Number built 6,000+
Developed from Lycoming T53
Developed into Lycoming ALF 502

The Honeywell T55 (formerly Lycoming; company designation LTC-4) is a turboshaft engine used on American helicopters and fixed-wing aircraft (in turboprop form) since the 1950s, and in unlimited hydroplanes since the 1980s. As of 2021, more than 6,000 of these engines have been built.[1] It is produced by Honeywell Aerospace, a division of Honeywell based in Phoenix, Arizona, and was originally designed by the Turbine Engine Division of Lycoming Engines in Stratford, Connecticut, as a scaled-up version of the smaller Lycoming T53. The T55 serves as the engine on several major applications including the CH-47-Chinook, the Bell 309, and the Piper PA-48 Enforcer. The T55 also serves as the core of the Lycoming ALF 502 turbofan. Since the T55 was first developed, progressive increases in airflow, overall pressure ratio, and turbine inlet temperature have more than tripled the power output of the engine.[2][3][4]


Civil and experimental variants

Turboprop engine with a power rating of 1,600 shp (1,200 kW) and dry weight of 695 lb (315 kg); was designated the YT55-L-1 after its 50-hour qualification test was completed in December 1957[5]
Geared turboshaft engine with an initial power rating of 1,800 shp (1,300 kW); completed a 50-hour qualification test demonstrating 2,050 shp (1,530 kW) in March 1958, and then was designated as the YT55-L-3 with a power rating of 1,900 shp (1,400 kW)[5]
Ungeared version of the LTC4B-2, with an integral oil cooler and tank; demonstrated 2,500 shp (1,900 kW) in January 1960; the higher power rating resulted from increased turbine inlet temperatures, which came from small modifications learned from YT55-L-1 and YT55-L-3 development experience; completed 50-hour qualification test at 2,200 shp (1,600 kW) power rating in February 1960, after which it was designated as the YT55-L-5; completed its 150-hour qualification test in September 1960, after which its designation changed from YT55-L-5 to the T55-L-5 production engine[5]
Civil designation for the T55-L-7 military engine; dry weight of 580 lb (260 kg)[5] also powered the original Bell 214 helicopter as a 2,930 shp (2,180 kW) engine in 1970[6]
2,950 shp (2,200 kW) engine powering the Bell 214A helicopter;[7] uprated from the T55-L-7C; 433 engines produced between 1973 and 1977 for this military helicopter[8]
similar to L-7 with two-stage gas generator turbine
Turboprop engine with a power rating of 4,600 shp (3,400 kW) and a weight of 680 lb (310 kg), 10 lb (4.5 kg) more than the T55-L-11 that it is derived from;[9] brake-specific fuel consumption (BSFC) of 0.504 lb/(hp⋅h) (307 g/kWh)[10]
Civil designation for the YT55-L-1A military turboprop engine[3]
Turboprop engine with a maximum and normal power rating of 2,445 and 2,100 shp (1,823 and 1,566 kW); high-performance version of the T55-L-1[11]
9-stage compressor
Turboprop engine with a power rating of 3,690 shp (2,750 kW), weight of 920 lb (420 kg), pressure ratio of 8.2:1, and a BSFC of 0.52 lb/(hp⋅h) (320 g/kWh)[12]
First experimental high-bypass turbofan engine produced in the United States, initially run in February 1964; two produced; used the engine core of the T55-L-7;[13] 40 in diameter (100 cm) geared fan stage, producing a static thrust of 4,320 lb (1,960 kg); predecessor of the ALF 502 and LF 507 production turbofans;[14] bypass ratio of 6:1; weight of 825 lb (374 kg)[15] maximum pressure ratio of 1.4:1 (fan) and 9.5:1 (engine), turbine inlet temperature of 1,810 °F (990 °C), maximum rated air flow for the gas generator and fan of 31.5 and 157.5 lb/s (14.3 and 71.4 kg/s), thrust-specific fuel consumption (TSFC) of 0.411 lb/(lbf⋅h) (11.6 g/(kN⋅s))[16]
Turbofan with T55 / LTC4K 9-stage compressor gas generator core
Turbofan based on the T55-L-7C turboshaft, producing 5,220 lbf (23.2 kN) of thrust; 66 in (1.7 m) length, 41 in (100 cm) fan diameter, 6:1 bypass ratio, 1,010 lb (460 kg) weight, TSFC of 0.41 lb/(lbf⋅h) (12 g/(kN⋅s))[17]
Turbofan based on the T55-L-11 turboshaft, producing 6,700 lbf (30 kN) of thrust; 66 in (1.7 m) length, 50 in (130 cm) fan diameter, 8.2:1 bypass ratio, 1,130 lb (510 kg) weight, TSFC of 0.36 lb/(lbf⋅h) (10 g/(kN⋅s))[17]
Certified September 16, 1975; dry weight 618 lb (280 kg);[18] 2,930 shp (2,180 kW) engine powering the Bell 214B helicopter, which was produced between 1976 and 1981;[6] 88 engines manufactured for that commercial helicopter;[8] commercial version of the LTC4-8D
Certified November 7, 1980; turboshaft engine with a sea-level power rating of 2,975 hp (2,218 kW) max continuous and 4,075 hp (3,039 kW) 5-minute takeoff; 30-minute power rating of 4,355 hp (3,248 kW) with one engine inoperative; dry weight 780 lb (350 kg);[18] used on the Boeing Model 234 (civilian version of the Chinook);[19] based on the T55-L-712; produced between 1979 and 1985, with 44 engines manufactured;[8] also used on the Boeing Model 360, a technology demonstrator helicopter, in 1987[20]

Military variants

Turboprop engine with a maximum and normal power rating of 1,600 and 1,325 shp (1,193 and 988 kW) and a pressure ratio of 6:1[21]
Turboprop version of the YT55-L-3, producing 1,850 shp (1,380 kW); length 58.85 in (149.5 cm), diameter 24.25 in (61.6 cm), dry weight 695 lb (315 kg), pressure ratio 6.5:1, air mass flow 20.5 lb/s (9.3 kg/s), BSFC 0.648 lb/(hp⋅h) (394 g/kWh)[3]
Turboshaft engine with a maximum and normal power rating of 1,900 and 1,700 shp (1,400 and 1,300 kW) and a pressure ratio of 6:1;[21] a geared engine that was initially selected to power the Army Chinook helicopter HC-1B (later designated as the CH-47A) in July 1958 by a joint Air Force/Army team[5]
Turboshaft engine with a maximum and normal power rating of 2,200 and 1,850 shp (1,640 and 1,380 kW) and a pressure ratio of 6:1; high-speed version of the T55-L-3[21] allowed for use on the Chinook instead of the geared YT55-L-3 engine due to August 1958 engine contract modification, with the reduction gearing now provided in the helicopter power transmission system instead of the engine; 570 lb (260 kg) weight engine; first delivered for the Chinook in August 1960; powered first flight of the Chinook in October 1961; selected for the Curtiss-Wright X-19 tiltrotor aircraft in August 1962;[5] 146 engines manufactured between 1960 and 1963 for the CH-47A[22]
Turboshaft engine with a power rating of 2,650 shp (1,980 kW) and a BSFC of 0.61 lb/(hp⋅h) (370 g/kWh);[23] completed 150-hour qualification test in September 1962 at a 2,650 shp (1,980 kW) power rating;[5]
Military and normal power rating of 2,650 and 2,200 shp (1,980 and 1,640 kW); used on the CH-47A[24]
Turboshaft engine with a maximum, military, and normal power rating of 2,850, 2,650, and 2,400 shp (2,130, 1,980, and 1,790 kW); used on the CH-47B;[24] BSFC of 0.6 lb/(hp⋅h) (360 g/kWh);[23] passed qualification testing in September 1966[25]
Turboprop engine with a power rating of 2,445 shp (1,823 kW), weight of 795 lb (361 kg), pressure ratio of 6.4:1, and a BSFC of 0.62 lb/(hp⋅h) (380 g/kWh); used on the Rockwell YAT-28E;[12] also powered Piper Enforcer prototype aircraft for flight tests in 1971 and 1983-1984[26]
Turboshaft engine with a maximum, military, and normal power rating of 3,750, 3,400, and 3,000 shp (2,800, 2,540, and 2,240 kW); used on the CH-47C;[24] BSFC of 0.52 lb/(hp⋅h) (320 g/kWh);[10] completed 50-hour preliminary flight rating test (PFRT) in May 1967[25]
3,750 shp (2,800 kW) turboshaft engine used on the CH-47D, with production starting in 1978; 849 engines manufactured by 1989[27]
4,110 shp (3,060 kW) turboshaft engine used on the MH-47E Chinook SOF[28]
4,777 shp (3,562 kW) turboshaft engine used on the CH-47F; low-rate initial production started in December 1997[29]
5,000 shp (3,729 kW)
6,000 shp (4,500 kW) turboshaft engine to be tested on an CH-47F testbed aircraft, offering a 25 percent increase in power output and 10 percent reduction in fuel consumption compared to the T55-GA-714A;[30] initial testing of the first engine began in November 2021[31]
6,000 shp (4,474 kW)
A 6,500 shp (4,800 kW) turboshaft engine upgrade kit proposed in 2008 for a 69,900 lb weight (31,700 kg) growth version of the Chinook[32]

General characteristics





Specifications (T55-L-714A)

See also

Related development

Comparable engines

Related lists


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