Pratt & Whitney Canada PW200
The Pratt & Whitney Canada PW200 is a series of shaft gas turbines for aviation, especially for the propulsion of helicopters . These engines are produced by Pratt & Whitney Canada .
Work on the type began in 1983. The first series-production variant was PW206A , which was approved in 1991 together with the PW206B variant. The engine consists of a single-stage centrifugal compressor that draws in the combustion air via an inlet located on the circumference, a combustion chamber with deflection and 12 injection nozzles, as well as an axial high-pressure turbine for the compressor drive and an axial low-pressure turbine for the shaft drive, which has a gear ratio of i = 6.634 is. All variants of the engine have a digital engine controller ( FADEC ), but if it fails, the turbine can also continue to operate via a conventional hydromechanical unit. An electric starter starts the engine. When the engine is started, the fuel is ignited by means of a dual ignition system.
Engines of this series 206 are used in the MD Helicopters Explorer , the Agusta A109 E, Bell 427 , Kazan Ansat and the Eurocopter EC 135 . The current (6/2006) are the PW207C / D / E engine variants, all of which have an integrated engine configuration management system .
The PW207K variant is intended for export to Russia and for use in Kazan Ansat. 20 engines of this variant were sold to Kazan in 2001.
The engine must be serviced after an operating time of 600 hours or once a year. The time between overhauls ( MTBO ) is 3000 hours (or 3500 hours for older engines) or 15,000 flight cycles.
With the latest variant PW210 (e.g. PW210S for the Sikorsky S-76 D) not only should more power be available, but consumption should also be reduced. This new variant is viewed by P&W as a new series, since compared to the PW200 it now has a two-stage centrifugal compressor and low-pressure turbine as well as a control system via double redundant FADEC . Approval is scheduled for 2009.
Technical data (overview)
| Type | Starting power kW |
Continuous power kW |
Length m |
Width m |
Height m |
Dry weight kg |
Max. Speed min-1 |
|---|---|---|---|---|---|---|---|
| PW206A | 463 | 410 | 0.93 | 0.54 | 0.62 | 107.5 | 6741 |
| PW206B | 321 | 321 | 1.04 | 0.52 | 0.73 | 118.9 | 6741 |
| PW206B2 | 321 | 321 | 1.04 | 0.52 | 0.73 | 117.2 | 6741 |
| PW206C | 418 | 418 | 0.93 | 0.54 | 0.62 | 107.5 | 6151 |
| PW206E | 482 | 426 | 0.93 | 0.54 | 0.62 | 113.7 | 6741 |
| PW207C | 426 | 426 | 0.93 | 0.54 | 0.62 | 113.7 | 6741 |
| PW207D | 426 | 426 | 0.93 | 0.54 | 0.62 | 113.7 | 6741 |
| PW207E | 482 | 426 | 0.93 | 0.54 | 0.62 | 113.7 | 6741 |
| PW210 | 570 (max. 745) | 1.09 | 0.50 | 0.60 | 6409 |
The PW206A engine has a compression of 8 and a specific consumption of 340 g / kWh at take-off power.