Lycoming T53: Difference between revisions

T53
Cutaway view of an early T53 turboprop, with single stage HP and power turbines
Type	Turboshaft
National origin	United States
Manufacturer	Lycoming Engines Honeywell Aerospace
First run	~1955
Major applications	AH-1 Cobra Kaman K-MAX OV-1 Mohawk UH-1 Iroquois
Developed into	Lycoming T55

The Lycoming T53, (company designation LTC-1) is a turboshaft engine used on helicopters and (as a turboprop) fixed-wing aircraft since the 1950s. It was designed at the Lycoming Turbine Engine Division in Stratford, Connecticut by a team headed by Anselm Franz, who was the chief designer of the Junkers Jumo 004 during World War II.

A much larger engine, similar in overall design, became the Lycoming T55. Both engines are now produced by Honeywell Aerospace.

Variants

Military designations

T53-L-1B

860 hp (645 kW)

T53-L-5

960 hp (720 kW)

T53-L-11

1100 shp (820 kW)

T53-L-13B

1400 shp (1044 kW) improved L-11

T53-L-701

1,400 hp (1044 kW) Turboprop variant used on Mohawk and AIDC T-CH-1

T53-L-703

1,800 hp (1343 kW) improved durability variant of the L-13B

Civil designations

T5311A

1100 shp (820 kW)

T5313A

1400 shp (1044 kW) commercial variant of the L-13

T5313B

1400 shp (1044 kW) commercial variant of the L-13

T5317A

1500 shp (1119 kW) improved variant of the L-13

LTC1K-4K

1550 shp (1156 kW) direct drive variant of the L-13B

Applications

• AIDC T-CH-1 (T53-L-701)
• AIDC XC-2
• Bell 204B (T5311A)
• Bell 205A (T5313B)
• Bell 205A-1 (T5313B and T5317A)
• Bell AH-1 Cobra (T53-L-703)
• Bell UH-1H Iroquois (T53-L-703)
• Bell XV-15 (LTC1K-4K)
• Boeing Vertol VZ-2 (YT53)
• Canadair CL-84
• Doak VZ-4
• F+W C-3605
• Grumman OV-1D Mohawk (T53-L-701)
• Kaman HH-43 Huskie
• Kaman K-1200 (T5317A)
• Kaman K-MAX
• Ryan VZ-3 Vertiplane
• DB Class 210, diesel railway locomotive

Specifications (T53-L-701)

Data from Flight International

General characteristics

• Type: Turboshaft
• Length: 58.4 in (1,483 mm)
• Diameter: 23 in (584 mm)
• Dry weight: 688 lb (312kg)

Components

• Compressor: 5-stage axial compressor and 1-stage centrifugal compressor
• Combustors: reverse flow
• Turbine: 2-stage high pressure turbine; 2-stage power turbine

Performance

• Maximum power output: 1,451 shp (1,082 kW)
• Overall pressure ratio: 7.4
• Air mass flow: 10.7 lb/s (4.853 kg/s)

References

• Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. p. 132. ISBN 0-7509-4479-X. {{cite book}}: Cite has empty unknown parameter: |coauthors= (help)

External links

• Honeywell T53 page
• Honeywell T53 Worldwide Parts Distributor page