General Electric T58: Difference between revisions

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,

Browse history interactively

← Previous edit

Content deleted Content added

VisualWikitext

Inline

Latest revision as of 23:35, 13 December 2023

The General Electric T58 is an American turboshaft engine developed for helicopter use. First run in 1955, it remained in production until 1984, by which time some 6,300 units had been built. On July 1, 1959, it became the first turbine engine to gain FAA certification for civil helicopter use. The engine was license-built and further developed by de Havilland in the UK as the Gnome, in the West Germany by Klöckner-Humboldt-Deutz,^[1] and also manufactured by Alfa Romeo and the IHI Corporation.

Design and development

Development commenced with a 1953 US Navy requirement for a helicopter turboshaft to weigh under 400 lb (180 kg) while delivering 800 hp (600 kW). The engine General Electric eventually built weighed only 250 lb (110 kg) and delivered 1,050 hp (780 kW) and was soon ordered into production. First flight was on a modified 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

^[5]

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-1 BLC 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)

Data from ^[9]^[10]

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

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

References

^ 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.).

External links

Minijets website

[1] Production Briefing. // Aviation Week & Space Technology, June 24, 1963, v. 78, no. 25, p. 79.

[2] Flying Magazine: 52. March 1960. {{cite journal}}: Missing or empty |title= (help)

[3] "gas generator | tw snalt | reduction gear | 1958 | 0077 | Flight Archive". www.flightglobal.com. Archived from the original on 2015-04-16.

[4] [1] Archived January 15, 2008, at the Wayback Machine

[5] "Military Turboshaft/Turboprop Specifications". www.jet-engine.net. Archived from the original on 2002-05-29.

[6] MiniJets Website Archived 2016-03-05 at the Wayback Machine Retrieved 28 June 2011

[7] 'Rodger Ward's Indy 500 Preview; Will the Turbines Takeover?'

[8] Engine Collection. NEAM. Retrieved on 2013-08-16.

[9] "About the General Electric T58 (series) Turbine Engine". Archived from the original on 2011-11-24.

[JAWA62-63-10] Taylor, John W.R. FRHistS. ARAeS (1962). Jane's All the World's Aircraft 1962-63. London: Sampson, Low, Marston & Co Ltd.

[1]

[2]

[3]

[4]

[5]

[6]

[7]

[8]

[9]

[10]

@@ Line 1: / Line 1: @@
+{{short description|American turboshaft engine for helicopters}}
 <!-- This article is a part of [[Wikipedia:WikiProject Aircraft]]. Please see [[Wikipedia:WikiProject Aircraft/page content]] for recommended layout. -->
-{|{{Infobox Aircraft Begin
+{|{{Infobox aircraft begin
  |name= T58
  |image= General Electric T58 turboshaft.jpg
@@ Line 9: / Line 10: @@
  |national origin = [[United States]]
  |manufacturer= [[GE Aviation]]
- |first run=April {{Avyear|1955}}
+ |first run=April 1955
- |major applications= [[Boeing Vertol CH-46 Sea Knight]] <br> [[Kaman SH-2 Seasprite]] <br> [[Sikorsky SH-3 Sea King]]
+ |major applications= [[Boeing Vertol CH-46 Sea Knight]] <br /> [[Kaman SH-2 Seasprite]] <br /> [[Sikorsky SH-3 Sea King]]
  |number built =
  |program cost =
@@ Line 19: / Line 20: @@
 }}
 |}
-[[File:US Navy 040422-N-9849W-049 Members assigned to the War Lords of Light Helicopter Anti-Submarine Squadron Five One (HSL-51) inspect a new engine.jpg|thumb|Inspection of a T58 engine before installation in a [[Sikorsky SH-3 Sea King|SH-3G Sea King]] helicopter]]
-The '''General Electric T58''' is an American [[turboshaft]] engine developed for helicopter use. First run in 1955, it remained in production until 1984, by which time some 6,300 units had been built. On July 1, 1959, it became the first turbine engine to gain FAA certification for civil helicopter use. The engine was license-built and further developed by [[de Havilland]] in the UK as the [[Rolls-Royce Gnome|Gnome]], and also manufactured by [[Alfa Romeo]] and the [[IHI Corporation]].
+The '''General Electric T58''' is an American [[turboshaft]] engine developed for helicopter use. First run in 1955, it remained in production until 1984, by which time some 6,300 units had been built. On July 1, 1959, it became the first turbine engine to gain FAA certification for civil helicopter use. The engine was license-built and further developed by [[de Havilland]] in the UK as the [[Rolls-Royce Gnome|Gnome]], in the [[West Germany]] by [[Klöckner-Humboldt-Deutz]],<ref>[https://archive.org/stream/Aviation_Week_1963-06-24#page/n39/mode/1up Production Briefing]. // ''Aviation Week & Space Technology'', June 24, 1963, v. 78, no. 25, p. 79.</ref> and also manufactured by [[Alfa Romeo]] and the [[IHI Corporation]].
 ==Design and development==
-Development commenced with a 1953 [[US Navy]] requirement for a helicopter turboshaft to weigh under 400&nbsp;lb (180&nbsp;kg) while delivering 800&nbsp;hp (600&nbsp;kW). The engine General Electric eventually built weighed only 250&nbsp;lb (110&nbsp;kg) and delivered 1,050&nbsp;hp (780&nbsp;kW) and was soon ordered into production. First flight was on a modified [[Sikorsky HSS-1]] in 1957, and civil certification for the '''CT58-100''' variant was obtained two years later.<ref>{{cite journal|magazine=Flying Magazine|date=March 1960|page=52}}</ref>
+Development commenced with a 1953 [[US Navy]] requirement for a helicopter turboshaft to weigh under 400&nbsp;lb (180&nbsp;kg) while delivering 800&nbsp;hp (600&nbsp;kW). The engine General Electric eventually built weighed only 250&nbsp;lb (110&nbsp;kg) and delivered 1,050&nbsp;hp (780&nbsp;kW) and was soon ordered into production. First flight was on a modified [[Sikorsky HSS-1]] in 1957, and civil certification for the '''CT58-100''' variant was obtained two years later.<ref>{{cite journal |journal=Flying Magazine |date=March 1960 |page=52}}</ref>
-A number of unusual features are incorporated into the T58:<ref>https://www.flightglobal.com/pdfarchive/view/1958/1958%20-%200077.html</ref>
+A number of unusual features are incorporated into the T58:<ref>{{cite web |url=https://www.flightglobal.com/pdfarchive/view/1958/1958%20-%200077.html |title=gas generator {{!}} tw snalt {{!}} reduction gear {{!}} 1958 {{!}} 0077 {{!}} Flight Archive |website=www.flightglobal.com |url-status=dead |archive-url=https://web.archive.org/web/20150416104905/http://www.flightglobal.com/pdfarchive/view/1958/1958%20-%200077.html |archive-date=2015-04-16}} </ref>
-) 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.
+*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.
-) compressor handling at part speed is facilitated by several rows of variable stators at the front part of the unit. This was a fairly novel feature when the engine was first introduced.
+*the combustor is a straight-through annular design, rather than reverse flow.
-) a single stage power turbine. which delivers power to the rear of engine. The hot exhaust stream is diverted sideways, away from the output shaft, by a skewed jet pipe.{{citation needed|date=March 2016}}
-) 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&nbsp;hp (1,044&nbsp;kW).  The most powerful version, the T58-GE-16, produces 1,870&nbsp;hp (1,390&nbsp;kW).<ref>[http://www.geae.com/engines/military/comparison_turboshaft.html ] {{webarchive |url=https://web.archive.org/web/20080115084011/http://www.geae.com/engines/military/comparison_turboshaft.html |date=January 15, 2008 }}</ref>
 ==Variants==
+[[File:US Navy 040422-N-9849W-049 Members assigned to the War Lords of Light Helicopter Anti-Submarine Squadron Five One (HSL-51) inspect a new engine.jpg|thumb|Inspection of a T58 engine before installation in a [[Sikorsky SH-3 Sea King|SH-3G Sea King]] helicopter]]
-ref="http://www.jet-engine.net/miltsspec.html"
+<ref>{{cite web |url=http://www.jet-engine.net/miltsspec.html |title=Military Turboshaft/Turboprop Specifications |website=www.jet-engine.net |url-status=dead |archive-url=https://web.archive.org/web/20020529032931/http://www.jet-engine.net/miltsspec.html |archive-date=2002-05-29}} </ref>
 ;T58-GE-1:{{convert|1290|hp|kW|abbr=on}}
 ;T58-GE-2:{{convert|1325|hp|kW|abbr=on}}
@@ Line 50: / Line 48: @@
 ;T58-GE-8F:{{convert|1350|hp|kW|abbr=on}}
 ;T58-GE-10:{{convert|1400|hp|kW|abbr=on}}
+;T58-GE-14:{{convert|1400|hp|kW|abbr=on}} 2-stage power turbine
 ;T58-GE-16:{{convert|1870|hp|kW|abbr=on}}
 ;T58-GE-100:{{convert|1500|hp|kW|abbr=on}}
 ;T58-GE-402:{{convert|1500|hp|kW|abbr=on}}
-;CT58-IHI-110-1:{{convert|1400|hp|kW|abbr=on}}
+;CT58-100-1:{{convert|1050|hp|kW|abbr=on}}
-;CT58-IHI-140-1:{{convert|1400|hp|kW|abbr=on}}
+;CT58-110-1:{{convert|1350|hp|kW|abbr=on}}
+;CT58-140-1:{{convert|1500|hp|kW|abbr=on}} commercial T58-GE-10
+;Ishikawajima-Harima CT58-IHI-110-1:{{convert|1400|hp|kW|abbr=on}}
+;Ishikawajima-Harima CT58-IHI-140-1:{{convert|1400|hp|kW|abbr=on}}
+;Ishikawajima-Harima T58-IHI-8B BLC:For [[Shin Meiwa PS-1]] BLC system
 ;[[Rolls-Royce Gnome]]:Licensed production and development of the T58 in the United Kingdom.
 ==Applications==
+{{Columns-list|
 * [[Aérospatiale Super Frelon|Aerospatiale SA 321K Super Frelon]] - Used by [[Israeli Air Force]]
 * [[Agusta A.101]]
@@ Line 66: / Line 69: @@
 * [[Boeing CH-46 Sea Knight]]
 * [[Fairchild VZ-5]] (YT58)
+* [[Kaman K-16B]]
 * [[Kaman SH-2 Seasprite]]
 * [[Piasecki XH-21D Shawnee]] (Model 71)
@@ Line 75: / Line 79: @@
 * [[Sikorsky S-67]]
 * [[Sikorsky S-72]]
+* [[Shin Meiwa US-1A]] for layer boundary control
+}}
-===Other Applications===
+===Other===
-Two T58s, converted to turbojets by the removal of the power turbines, were used as the engines on the [[Maverick TwinJet 1200]].<ref>[http://minijets.org/typo3/index.php?id=89 MiniJets Website] Retrieved 28 June 2011</ref>
+Two T58s, converted to turbojets by the removal of the power turbines, were used as the engines on the [[Maverick TwinJet 1200]].<ref>[http://minijets.org/typo3/index.php?id=89 MiniJets Website] {{Webarchive|url=https://web.archive.org/web/20160305025159/http://minijets.org/typo3/index.php?id=89 |date=2016-03-05 }} Retrieved 28 June 2011</ref>
-The [[Carroll Shelby]] turbine cars entered in the 1968 Indianapolis 500 race were powered by T58s.<ref>[https://books.google.com/books?id=FtQDAAAAMBAJ&pg=PA98&dq=wallis+turbine+car&hl=en&ei=7b4HTs6lHJTSsAOUivHdDQ&sa=X&oi=book_result&ct=result&resnum=2&ved=0CC4Q6AEwAQ#v=onepage&q=wallis%20turbine%20car&f=false 'Rodger Ward's Indy 500 Preview; Will the Turbines Takeover?']</ref> The cars were found to be using variable inlets to get around the USAC regulations on the maximum allowable inlet size and were disqualified.
+The [[Carroll Shelby]] turbine cars entered in the 1968 Indianapolis 500 race were powered by T58s.<ref>[https://books.google.com/books?id=FtQDAAAAMBAJ&dq=wallis+turbine+car&pg=PA98 'Rodger Ward's Indy 500 Preview; Will the Turbines Takeover?']</ref> The cars were found to be using variable inlets to get around the USAC regulations on the maximum allowable inlet size and were disqualified.
-Turboshaft engines like the GE T58, Lycoming T53/T55 are also used to power high performance powerboats, such as aport and offshore vee, and catamaran hulls like the Skater "Jet Set" or Mystic Powerboats "My Way", water jet river racers like Unnatural Dissaster and hydroplanes. Some of these boats run in excess of 200&nbsp;mph, despite them being open cockpit pleasure boats.
+==Engines on display==
-==Survivors==
 * There is a YT58-GE-2A cutaway on display at the [[New England Air Museum]], [[Bradley International Airport]], Windsor Locks, CT <ref>[http://neam.org/index.php?option=com_content&view=article&id=1104 Engine Collection]. NEAM. Retrieved on 2013-08-16.</ref>
@@ Line 90: / Line 94: @@
 <!-- If you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] -->
 <!-- Please include units where appropriate (main comes first, alt in parentheses). If data are missing, leave the parameter blank (do not delete it). For additional lines, end your alt units with )</li> and start a new, fully-formatted line with <li> -->
-|ref=<ref>{{cite web|title=About the General Electric T58 (series) Turbine Engine|url=http://www.turbinefun.com/T58-GE-3.asp}}</ref><ref name=JAWA62-63>{{cite book|last=Taylor|first=John W.R. FRHistS. ARAeS|title=Jane's All the World's Aircraft 1962-63|year=1962|publisher=Sampson, Low, Marston & Co Ltd|location=London}}</ref>
+|ref=<ref>{{cite web |title=About the General Electric T58 (series) Turbine Engine |url=http://www.turbinefun.com/T58-GE-3.asp |url-status=dead |archiveurl=https://web.archive.org/web/20111124053014/http://www.turbinefun.com/T58-GE-3.asp |archivedate=2011-11-24 }}</ref><ref name=JAWA62-63>{{cite book|last=Taylor|first=John W.R. FRHistS. ARAeS|title=Jane's All the World's Aircraft 1962-63|year=1962|publisher=Sampson, Low, Marston & Co Ltd|location=London}}</ref>
-|type=Free power turbine turboshaft
+|type=[[Free-turbine turboshaft|Free power turboshaft]]
 |length={{convert|55|in|mm|abbr=on|0}}
 |diameter={{convert|16|in|mm|abbr=on|0}}
+|weight= {{ubl
-|weight={{convert|285|lb|kg|abbr=on|0}} without reduction gearbox, {{convert|391|lb|kg|abbr=on|0}} with reduction gearbox
+ | {{convert|285|lb|kg|abbr=on|0}} without [[reduction gearbox]],
-|compressor=10 stage axial-flow compressor with variable inlet guide vanes + variable incidence stators in first three stages
+ | {{convert|391|lb|kg|abbr=on|0}} with reduction gearbox
-|combustion=Annular combustion chamber with 16 burner nozzles on two manifolds
+ }}
-|turbine=2x gas generator turbine stages + 1x free power turbine stage
+|compressor=10-stage [[axial compressor|axial-flow]] [[compressor]] with variable inlet guide vanes, and variable incidence stators in first three stages
-|fueltype=Aviation kerosene
+|combustion=[[Combustor#Annular|Annular combustion chamber]] with 16 burner nozzles on two manifolds
+|turbine= {{ubl
+ | 2× [[gas generator]] turbine stages and
+ | 1× free power turbine stage
+ }}
+|fueltype=[[Jet fuel|Aviation kerosene]]
 |oilsystem=
 |power={{convert|1,250|hp|kW|abbr=on|2}}
@@ Line 104: / Line 114: @@
 |compression=8.3:1
 |bypass=
-|aircon={{convert|12.4|lb|kg|abbr=on|2}}/sec at 26,300rpm
+|aircon={{convert|12.4|lb/s|kg/s|abbr=on|2}} at 26,300 rpm
 |turbinetemp=
 |fuelcon=
-|specfuelcon=0.64 lb/hp/hr (0.389 kg/kW/hr) at maximum continuous rating
+|specfuelcon={{convert|0.64|lb/hp.h|kg/kW.h|abbr=on}} at maximum continuous rating
-|power/weight=6.1 hp/lb (10.024 kW/kg) without reduction gearbox
+|power/weight={{convert|6.1|hp/lb|kW/kg|abbr=on}} without reduction gearbox
 |thrust/weight=
 }}
 ==See also==
+{{Portal|Aviation}}
 {{aircontent
 <!-- other related articles that have not already linked: -->
@@ Line 136: / Line 147: @@
 {{reflist}}
 * {{cite book |last= Gunston |first= Bill |title=World Encyclopedia of Aero Engines |year=1986 |publisher=Patrick Stephens |location= Wellingborough |page=65 }}
-* [http://www.geae.com/engines/military/t58/index.html GE Aviation T58 page] and [http://www.geae.com/engines/military/t58/spotlight_history.html T58 history page]
+* [http://www.geae.com/engines/military/t58/index.html GE Aviation T58 page] {{Webarchive|url=https://web.archive.org/web/20110620063707/http://www.geae.com/engines/military/t58/index.html |date=2011-06-20 }} and [http://www.geae.com/engines/military/t58/spotlight_history.html T58 history page] {{Webarchive|url=https://web.archive.org/web/20100926013306/http://www.geae.com/engines/military/t58/spotlight_history.html |date=2010-09-26 }}
+*{{cite report |work=[[Federal Aviation Administration]] (FAA) |series=Type Certificate Data Sheet |author=[[General Electric]] |date=September 4, 2018 |title=1E3 |edition=16th |url=https://drs.faa.gov/browse/excelExternalWindow/2d4a5aa5-53a3-4ab4-9d2b-f2bd6df545c0}}
+*{{cite report |work=[[Federal Aviation Administration]] (FAA) |series=Type Certificate Data Sheet |author=[[Ishikawajima-Harima]] |date=August 10, 1970 |title=E1PC |edition=1st |url=https://drs.faa.gov/browse/excelExternalWindow/cdd8da03-b6c7-4d98-9453-2c471f89b8b6}}
 ==External links==
-*[http://www.minijets.org/index.php?id=86 Minijets website]
+*[https://web.archive.org/web/20160313221448/http://www.minijets.org/index.php?id=86 Minijets website]
 {{GE aeroengines}}
 {{USAF gas turbine engines}}
-{{aeroengine-specs}}
 [[Category:General Electric aircraft engines|T58]]
-[[Category:Turboshaft engines 1950–1959]]
+[[Category:1950s turboshaft engines]]

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