Europrop TP400

The EPI TP400 is one of the military transport aircraft Airbus A400M innovative new turboprop engine of the manufacturer consortium Europrop International. The full name is due to the execution as TurboProp and development for the Airbus A400M Europrop International ( EPI) TP400- D6. The engine develops 11,000 shaft horsepower ( 8,203 kW), making it one of the most powerful engines of its kind

Development

The development of this engine ITP, MTU Aero Engines, Rolls -Royce and Snecma Moteurs are involved. For the development, manufacture and support of the TP400 -D6, the Joint Undertaking Europrop International was founded by the partner companies.

The first run of the engine was carried out on 28 October 2005, the admission was planned for mid-2008. Due to various problems ( with the bladed disks, the transmission, a "pumping" of the high-pressure compressor, the FADEC system), the approval was delayed repeatedly; according to the state in mid-2009 the head of the association of producers went to authorization by the end of 2009. The first flight on a modified C130W2 on 17 December 2008, the airfield Cambridge.

The successful first flight of the equipped with four TP400 -D6 engines Airbus A400M on December 11, 2009 in Seville.

In May 2011, the European Aviation Safety Agency ( EASA) granted approval for the TP400 -D6 turboprop -. It is the first military engine, to receive registration of commercial aviation.

Efficiency

The performance of the engine is the world only by the already relatively old by former Junkers professionals developed by Ferdinand Brandner Soviet engine Kuznetsov NK -12 ( inter alia, in the Antonov An-22 ), and the Ukrainian Ivchenko Progress D -27 (built- in the Antonov An -70) exceeded. Both engines feature in contrast to TP400 on two counter-rotating propellers.

Responsible for the project

Rolls- Royce

  • High-pressure compressor
  • Low-pressure shaft
  • Intermediate housing
  • Engine mechanics ( Parts )
  • Propulsion integration
  • Management Accounting

MTU

  • Medium pressure compressor
  • Medium -pressure turbine and shaft
  • Final assembly of all TP400 -D6
  • FADEC software
  • Development and production tests

Snecma

  • Combustion chamber
  • High-pressure turbine
  • Cultivation gear
  • Starter
  • Engine mounting on the aircraft

ITP

  • LPT
  • Front Cover
  • Nozzle
  • Turbine housing
  • External lines

Specifications

The engine is a three-shaft engine. The compressor reached a total pressure ratio of 25:1 and consists of a medium-pressure compressor ( five stages, pressure ratio 3.5:1 ) and a high pressure compressor ( six stages, pressure ratio 7:1). The turbine is divided into a respective single-stage high-and medium -pressure turbine as well as a three-stage low-pressure turbine which drives a reduction gear of the variable-pitch propeller Ratier petalled - FH386 Figeac. This consists of composite materials and has the possibility of the thrust reverser. The flanged reduction gear with a housing made ​​of magnesium alloy has a reduction ratio of 1:9,929. There are different gear for right - and left-handed propellers available, since the use of the A400M requires different senses of rotation of the propellers.

Industria de Turbo Propulsores Blisk Kuznetsov NK-12
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