Rolls-Royce AE 2100

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Template:Short description Template:Use dmy dates Template:Use American English

Template:Infobox aircraft engine

The Rolls-Royce AE 2100 is a turboprop developed by Allison Engine Company, now part of Rolls-Royce North America. The engine was originally known as the GMA 2100, when Allison was a division of former corporate parent General Motors.

Development

On July 11, 1989, Saab-Scania A.B. selected the GMA 2100 to power its new Saab 2000, a 50-seat stretch of the Saab 340 turboprop, in a US$500 million deal.[1] In July 1990, Industri Pesawat Terbang Nusantara (IPTN) of Indonesia picked the GMA 2100 as the engine for the twin-engine N-250 regional airliner.[2] Flight testing with a Template:Cvt Dowty R373 propeller on a Lockheed P-3 Orion testbed aircraft began on August 23, 1990, and finished after over 50 hours of flight and ground testing.[3]

The GMA 2100D3 became the powerplant for the Lockheed Martin C-130J Super Hercules. It made its first test flight on March 19, 1994,[4] which was conducted by Marshall Aerospace on a Lockheed C-130K Hercules testbed leased from the Royal Air Force. Testing ended in June 1994 after 47 flight hours.[5] The engine powered the initial flight of the C-130J aircraft on April 5, 1996.[6] By April 1997, the D3 variant had received Federal Aviation Administration (FAA) type certification.[7] 2,000 of the D3 variants have been delivered as of 2018.[8]

The engine's C variant was certified on December 20, 1993.[9] It powered the N-250 prototype's first flight on August 10, 1995,[10] but the N-250 aircraft program was postponed indefinitely in the late 1990s due to the Asian financial crisis.[11]

In June 1997, the AE 2100 was selected by Lockheed Martin and Alenia to power the C-27J Spartan tactical airlifter.[12] In October 2015, Alenia announced plans to use a Template:Convert uprated version of the AE 2100 as the baseline engine by 2017.[13]

Design

File:C-130 Hercules over Santa Cruz Island.jpg
C-130J Hercules with six-bladed props

A derivative of the Allison AE 1107C-Liberty (Rolls-Royce T406) turboshaft engine, the AE 2100 shares the same high-pressure core as that engine, as does the Rolls-Royce AE 3007 turbofan. This core is capable of powering turboprops of up to Template:Cvt.[14] The AE 2100 is a two-shaft design,Template:R and it was the firstTemplate:When to use dual FADECs (full authority digital engine control) to control both engine and propeller,[15] allowing both to be adjusted with a single lever.Template:R There are four production variants of the engine: the civil AE 2100A, and the military variants which include the AE 2100D2/D2A, AE 2100D3, AE 2100J and AE 2100P.

The AE 2100 inherited the Allison T56's 14-stage axial compressor design, but the inlet and the stator for the first five stages have variable blades. The annular combustor has 16 air-blast fuel injection nozzles. The turbine that drives the compressor has two stages, with the first stage using single-crystal blades. A free power turbine with two stages drives the propeller through an inner shaft and a gearbox.Template:R The engine has replaceable steel blades and vanes, which are more reliable but heavier than titanium.[14]

The AE 2100 engine and gearbox are rated at Template:Convert, but was derated to Template:Cvt for the Saab 2000, Lockheed Martin C-130J Super Hercules, and IPTN N-250, respectively.[16] The engine uses six-bladed, all-composite blade Dowty propellers, including the model R381 on the Saab 2000, R414 on the ShinMaywa US-2,[15] R384 on the IPTN N-250,[17] and R391 on the C-130J military transport[18] and the LM-100J civil-certified version of the C-130J.[19] The gearbox has a reduction ratio of about 14 and a mean time before unscheduled removal (MTBUR) of over 35,000 hours.[20]

Variants and applications

AE 2100A
AE 2100C
AE 2100D2A
AE 2100D3
AE 2100F
A variant proposed in 1995 and paired with Dowty R394 propellers to retrofit the Allison T56-powered Lockheed C-130 models E through H and Lockheed L-100-30, at a price after engine/propeller trade-in of USD$11 million per aircraft.[21]
AE 2100G
A variant offered in 1994 for the proposed ATR 82, a twin-turboprop airliner seating up to 86 passengers and requiring about Template:Cvt of power.[22]
AE 2100H
A variant offered in 1996 for Dassault Aviation's proposed Atlantic Third Generation (ATL3G) maritime patrol aircraft (MPA).[23]
AE 2100J
A hybrid of the AE 2100A and AE 2100D3, sporting the torque-meter and interconnecting struts from the AE 2100A and the gearbox-mounted accessory gearbox from the AE 2100D3; also uses a stronger reduction gearbox, a Dowty six-bladed propeller for higher loads, and modified inlet and bypass section positioning to mitigate seawater ingestion;[24] powers the ShinMaywa US-2.
AE 2100P
AE 2100SD-7
A variant proposed in 1994 for the European Future Large Aircraft[25] (which eventually became the Airbus A400M), with the required power increase from Template:Cvt estimated to cost USD$600 million.[26]

Specifications (AE 2100D3)

File:Rolls-Royce AE 2100D3 turboprops of a C-130J 2010.jpg
The AE 2100D3 engines of a US Air Force C-130J Hercules ready for inspection at Ramstein Air Base, Germany
File:JMSDF US-2 Rolls-Royce AE2100J turboprop engine left side view at MCAS Iwakuni May 5, 2019.jpg
A side view of the AE 2100J engine without its casing, on display at Marine Corps Air Station Iwakuni in 2019

Data from FAA type certificate data sheet no. TE1CH.[27]

General characteristics

Components

Performance

See also

Script error: No such module "Portal". Related development

Comparable engines

Related lists

References

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Bibliography

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External links

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Template:Allison aeroengines Template:Rolls-Royce plc aeroengines Template:USAF gas turbine engines

  1. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named NYT19890712
  2. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FI19900718
  3. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named DowtyNews199102
  4. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named DODAppropriations1995
  5. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FI19940831
  6. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FG19960416
  7. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named DD19970410
  8. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named 2thousandD3engines
  9. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named CRAN19940221
  10. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FG19950815
  11. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named AIN200110
  12. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named DD19970620
  13. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FG20151019
  14. ↑ a b Cite error: Invalid <ref> tag; no text was provided for refs named CAI199111p19
  15. ↑ a b Cite error: Invalid <ref> tag; no text was provided for refs named Dowty80
  16. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named Interavia199410p16
  17. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named CRAN19941114
  18. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FI19960828
  19. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named AADT_LM-100J
  20. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named CAI199111p12
  21. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FG19951212
  22. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named JPRS-EST-94-017
  23. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FG19960521
  24. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FI19970820
  25. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named JPRS-EST-94-014-L
  26. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named Interavia199410p14
  27. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named FAA_TCDS
  28. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named NRC2007
  29. ↑ Cite error: Invalid <ref> tag; no text was provided for refs named HectoPressure
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