Rolls-Royce Turbomeca RTM322



































RTM322

Salon du Bourget 20090619 248.jpg
RTM322 cutout at Le Bourget 2009
Type
Turboshaft
Manufacturer
Rolls-Royce Turbomeca Limited
First run
 15 December 1984[1]

Major applications
AgustaWestland Apache
AgustaWestland AW101
NHI NH90

Program cost
 £100 million (1985)[1]

Developed into
Safran Aneto

The Rolls-Royce Turbomeca RTM322 is a turboshaft engine produced by Rolls-Royce Turbomeca Limited, a joint venture between Rolls-Royce plc and Turbomeca. The engine was designed to suit a wide range of military and commercial helicopter designs. The RTM322 can also be employed in maritime and industrial applications.




Contents






  • 1 Development


  • 2 Applications


  • 3 Specifications (Mk 250 or 02/8 variant)


    • 3.1 General characteristics


    • 3.2 Components


    • 3.3 Performance




  • 4 See also


  • 5 References


  • 6 External links





Development


It was designed for the Hughes AH-64 Apache and Sikorsky Blackhawk, competing with the GE T700 and the Pratt & Whitney Canada PW100.
The partners shared equally the £100 million development costs, Rolls-Royce makes the turbines, the combustor, and the inlet particle separator while Turbomeca produces the axi-centrifugal compressor and intake.
It first ran on 15 December 1984, with eight bench prototypes for 30,000 cycles and 13,000 test hours, and four for flight tests, initially aiming for a 1987 certification.[1]


The first order for the RTM322 was received in 1992 to power 44 Royal Navy Merlin HM1s which subsequently entered service in 1998.[2]
Over 1,100 engines are in service, having logged over one million flight hours, powering 60% of the AW101 fleet and 80% of in-service NH90s.[3]


In 2013, Turbomeca acquired the entire program, becoming responsible for both production and product support.[3] Turbomeca's successor, Safran Helicopter Engines, developed it in the Aneto.



Applications



  • AgustaWestland Apache

  • AgustaWestland AW101

  • NHIndustries NH90

  • Also used in Eurocopter X3



Specifications (Mk 250 or 02/8 variant)


General characteristics




  • Type: Turboshaft


  • Length: 46.1 in (1.17 m)


  • Diameter: 25.5 in (0.65 m)


  • Dry weight: 503 lb (228 kg)


Components




  • Compressor: 3-stage axial + 1-stage centrifugal


  • Combustors: reverse flow


  • Turbine: 2-stage HP + 2-stage Power Turbine


Performance




  • Maximum power output: 2,270 shp (1,693 kW)


  • Overall pressure ratio: 14.2


  • Power-to-weight ratio: 7.4 kW/kg



See also



Related development


  • Safran Aneto


Comparable engines



  • General Electric T700

  • Pratt & Whitney Canada PW100


Related lists


  • List of aircraft engines


References





  1. ^ abc "First RTM 322 runs" (PDF). Flight International. 5 January 1985..mw-parser-output cite.citation{font-style:inherit}.mw-parser-output .citation q{quotes:"""""""'""'"}.mw-parser-output .citation .cs1-lock-free a{background:url("//upload.wikimedia.org/wikipedia/commons/thumb/6/65/Lock-green.svg/9px-Lock-green.svg.png")no-repeat;background-position:right .1em center}.mw-parser-output .citation .cs1-lock-limited a,.mw-parser-output .citation .cs1-lock-registration a{background:url("//upload.wikimedia.org/wikipedia/commons/thumb/d/d6/Lock-gray-alt-2.svg/9px-Lock-gray-alt-2.svg.png")no-repeat;background-position:right .1em center}.mw-parser-output .citation .cs1-lock-subscription a{background:url("//upload.wikimedia.org/wikipedia/commons/thumb/a/aa/Lock-red-alt-2.svg/9px-Lock-red-alt-2.svg.png")no-repeat;background-position:right .1em center}.mw-parser-output .cs1-subscription,.mw-parser-output .cs1-registration{color:#555}.mw-parser-output .cs1-subscription span,.mw-parser-output .cs1-registration span{border-bottom:1px dotted;cursor:help}.mw-parser-output .cs1-ws-icon a{background:url("//upload.wikimedia.org/wikipedia/commons/thumb/4/4c/Wikisource-logo.svg/12px-Wikisource-logo.svg.png")no-repeat;background-position:right .1em center}.mw-parser-output code.cs1-code{color:inherit;background:inherit;border:inherit;padding:inherit}.mw-parser-output .cs1-hidden-error{display:none;font-size:100%}.mw-parser-output .cs1-visible-error{font-size:100%}.mw-parser-output .cs1-maint{display:none;color:#33aa33;margin-left:0.3em}.mw-parser-output .cs1-subscription,.mw-parser-output .cs1-registration,.mw-parser-output .cs1-format{font-size:95%}.mw-parser-output .cs1-kern-left,.mw-parser-output .cs1-kern-wl-left{padding-left:0.2em}.mw-parser-output .cs1-kern-right,.mw-parser-output .cs1-kern-wl-right{padding-right:0.2em}


  2. ^ "RTM322". Rolls-Royce plc. Retrieved 2009-03-16.


  3. ^ ab "RTM322". Over 2,000 shp Propulsion solution. Safran Helicopter Engines.




External links







  • Rolls-Royce RTM322 page

  • Turbomeca RTM 322 page









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