General Electric T58
| T58 | |
|---|---|
| |
| Type | Turboshaft |
| National origin | United States |
| Manufacturer | GE Aviation
|
| First run | April 1955 |
| Major applications | Boeing Vertol CH-46 Sea Knight Kaman SH-2 Seasprite Sikorsky SH-3 Sea King |
| Variants | Rolls-Royce Gnome, |
The General Electric T58 is an American
.Design and development
Development commenced with a 1953
Sikorsky HSS-1 in 1957, and civil certification for the CT58-100 variant was obtained two years later.[2]
A number of unusual features are incorporated into the T58:[3]
- an all-axial compressor. Most other turboshafts in this power bracket have a centrifugal unit as a final compressor stage. As a result, the blades at the rear of the compressor are very small (less than 0.5in high) and extremely thin.
- compressor handling at part speed is facilitated by several rows of variable pitch stators at the front part of the unit. This was a fairly novel feature when the engine was first introduced.
- a single stage power turbine. which delivers power to the rear of the engine. The hot exhaust stream is diverted sideways, away from the output shaft.
- the combustor is a straight-through annular design, rather than reverse flow.
The main production version of the engine was the T58-GE-10, developing 1,400 hp (1,044 kW). The most powerful version, the T58-GE-16, produces 1,870 hp (1,390 kW).[4]
Variants
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- T58-GE-1
- 1,290 hp (960 kW)
- T58-GE-2
- 1,325 hp (988 kW)
- T58-GE-3
- 1,290 hp (960 kW)
- T58-GE-4
- T58-GE-5
- 1,500 hp (1,100 kW)
- T58-GE-6
- 1,250 hp (930 kW)
- T58-GE-8B
- 1,250 hp (930 kW)
- T58-GE-8E
- 1,350 hp (1,010 kW)
- T58-GE-8F
- 1,350 hp (1,010 kW)
- T58-GE-10
- 1,400 hp (1,000 kW)
- T58-GE-14
- 1,400 hp (1,000 kW) 2-stage power turbine
- T58-GE-16
- 1,870 hp (1,390 kW)
- T58-GE-100
- 1,500 hp (1,100 kW)
- T58-GE-402
- 1,500 hp (1,100 kW)
- CT58-100-1
- 1,050 hp (780 kW)
- CT58-110-1
- 1,350 hp (1,010 kW)
- CT58-140-1
- 1,500 hp (1,100 kW) commercial T58-GE-10
- Ishikawajima-Harima CT58-IHI-110-1
- 1,400 hp (1,000 kW)
- Ishikawajima-Harima CT58-IHI-140-1
- 1,400 hp (1,000 kW)
- Ishikawajima-Harima T58-IHI-8B BLC
- For Shin Meiwa PS-1BLC system
- Rolls-Royce Gnome
- Licensed production and development of the T58 in the United Kingdom.
Applications
- Aerospatiale SA 321K Super Frelon - Used by Israeli Air Force
- Agusta A.101
- AgustaBell AB204B
- Bell UH-1F/TH-1F
- Bell X-22 (YT58)
- Boeing CH-46 Sea Knight
- Fairchild VZ-5 (YT58)
- Kaman K-16B
- Kaman SH-2 Seasprite
- Piasecki XH-21D Shawnee(Model 71)
- Sikorsky SH-3 Sea King
- Sikorsky HH-3B/C/E/F
- Sikorsky HH-52 Seaguard
- Sikorsky S-61L/N
- Sikorsky S-62
- Sikorsky S-67
- Sikorsky S-72
- Shin Meiwa US-1A for layer boundary control
Other
Two T58s, converted to turbojets by the removal of the power turbines, were used as the engines on the Maverick TwinJet 1200.[6]
The Carroll Shelby turbine cars entered in the 1968 Indianapolis 500 race were powered by T58s.[7] The cars were found to be using variable inlets to get around the USAC regulations on the maximum allowable inlet size and were disqualified.
Engines on display
- There is a YT58-GE-2A cutaway on display at the New England Air Museum, Bradley International Airport, Windsor Locks, CT [8]
Specifications (T58-GE-8)
General characteristics
- Type: Free power turboshaft
- Length: 55 in (1,397 mm)
- Diameter: 16 in (406 mm)
- Dry weight:
- 285 lb (129 kg) without reduction gearbox,
- 391 lb (177 kg) with reduction gearbox
- 285 lb (129 kg) without
Components
- Compressor: 10-stage axial-flow compressor with variable inlet guide vanes, and variable incidence stators in first three stages
- Combustors: Annular combustion chamber with 16 burner nozzles on two manifolds
- Turbine:
- 2× gas generator turbine stages and
- 1× free power turbine stage
- Fuel type: Aviation kerosene
Performance
- Maximum power output: 1,250 hp (932.12 kW)
- Overall pressure ratio: 8.3:1
- Air mass flow: 12.4 lb/s (5.62 kg/s) at 26,300 rpm
- Specific fuel consumption: 0.64 lb/(hp⋅h) (0.39 kg/(kW⋅h)) at maximum continuous rating
- Power-to-weight ratio: 6.1 hp/lb (10.0 kW/kg) without reduction gearbox
See also
Related development
Related lists
References
Wikimedia Commons has media related to General Electric T58.
- ^ Production Briefing. // Aviation Week & Space Technology, June 24, 1963, v. 78, no. 25, p. 79.
- ^ Flying Magazine: 52. March 1960.
{{cite journal}}: Missing or empty|title=(help) - ^ "gas generator | tw snalt | reduction gear | 1958 | 0077 | Flight Archive". www.flightglobal.com. Archived from the original on 2015-04-16.
- ^ [1] Archived January 15, 2008, at the Wayback Machine
- ^ "Military Turboshaft/Turboprop Specifications". www.jet-engine.net. Archived from the original on 2002-05-29.
- ^ MiniJets Website Archived 2016-03-05 at the Wayback Machine Retrieved 28 June 2011
- ^ 'Rodger Ward's Indy 500 Preview; Will the Turbines Takeover?'
- ^ Engine Collection. NEAM. Retrieved on 2013-08-16.
- ^ "About the General Electric T58 (series) Turbine Engine". Archived from the original on 2011-11-24.
- ^ Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.
- Gunston, Bill (1986). World Encyclopedia of Aero Engines. Wellingborough: Patrick Stephens. p. 65.
- GE Aviation T58 page Archived 2011-06-20 at the Wayback Machine and T58 history page Archived 2010-09-26 at the Wayback Machine
- General Electric (September 4, 2018). 1E3. Federal Aviation Administration (FAA) (Report). Type Certificate Data Sheet (16th ed.).
- Ishikawajima-Harima (August 10, 1970). E1PC. Federal Aviation Administration(FAA) (Report). Type Certificate Data Sheet (1st ed.).