Pratt & Whitney PW6000

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Pratt & Whitney PW 6000.jpg
Type Turbofan
Manufacturer Pratt & Whitney
First run 21 August 2000
Major applications Airbus A318

The Pratt & Whitney PW6000 is a high-bypass turbofan engine designed for the Airbus A318 with a design thrust range of 18,000 to 24,000 lbf (82 to 109 kN).

Design and development[edit]

Pratt & Whitney designed the engine with minimum complexity to significantly reduce maintenance cost and achieve weight and fuel consumption savings. However, tests revealed that the initial five-stage high compressor based design did not meet promised fuel burn performance. As a result many of the original customers switched their orders to the rival CFM International CFM56-5. To address the problem, Pratt & Whitney re-certified an updated design utilizing a six-stage high compressor designed by MTU Aero Engines in order to achieve promised performance. The German company manufactures the high-pressure compressor and the low-pressure turbine. The HP compressor is driven by a single-stage turbine. On the LP spool a three-stage turbine drives a single-stage fan and a four-stage LP compressor.

The engine made its first flight August 21, 2000 on a test aircraft flown from Plattsburgh International Airport (KPBG), successfully completing a one-hour-and-20-minute flight.[1] The engine final assembly line is located at MTU Aero Engines at their location in Hanover, Germany.

LAN Airlines confirmed an order for 15 Airbus A318 aircraft, for a total of 34 engines (30 installed and 4 spares) powered by PW-6000 engines on 15 August 2005. In addition, LAN signed with Pratt and Whitney to power up to 25 option aircraft. If LAN exercises all options it would mean an additional 56 (50 installed and six spare) engines.

Prior to the LAN order, 84 CFM56-5 powered Airbus A318 aircraft had been ordered, with 28 currently in service as of December 2005.


A PW6000-equipped Airbus A318


Data from [2]

General characteristics

  • Type: Two spool high bypass ratio Turbofan
  • Length: 108 in (2.74 m)
  • Diameter: 56.5 in (1.44 m)
  • Dry weight: 5046 lbs (2289 kg)


  • Compressor: single stage fan, 4 stage low pressure compressor, 6 stage high pressure compressor
  • Combustors: Annular
  • Turbine: single stage high pressure turbine, 3 stage low pressure turbine


See also[edit]

Comparable engines
Related lists


  1. ^ "PW6000 Makes First Flight - Press Release". United Technologies. 2000-08-21. Retrieved 2012-08-23. 
  2. ^ "PW6000 Fact Sheet" (PDF). United Technologies. Retrieved 2012-08-23. 

External links[edit]