Pratt & Whitney Canada PW200
| PW200 | |
|---|---|
| Type | Turboshaft |
| National origin | Canada |
| Manufacturer | Pratt & Whitney Canada |
| Major applications | AgustaWestland AW109 Bell 429 Eurocopter EC135 MD Explorer Sikorsky S-76D |
|
| |
The Pratt & Whitney Canada PW200 is a family of turbine engines developed specifically for helicopter applications. It entered service in the 1990s.
Variants
- PW206A
- Maximum continuous power 550 shp (410 kW) [1] for use on the MD Explorer
- PW206B
- Maximum continuous power 431 shp (321 kW),[1] for use on the Eurocopter EC135
- PW206B2
- Maximum continuous power 431 shp (321 kW).[1]
- PW206C
- Maximum continuous power 561 shp (418 kW),[1] for use on the Agusta A109 Power
- PW206E
- Maximum continuous power 572 shp (427 kW).[1] for use on the MD Explorer
- PW207C
- Maximum continuous power 572 shp (427 kW).[1]
- PW207D
- Maximum continuous power 572 shp (427 kW).[1]
- PW207D1
- Variant of the PW207 with increased mechanical power, maximum continuous power 610 shp (450 kW).[1]
- PW207D2
- Variant of the PW207D1 with a fuel heater installed, maximum continuous power 610 shp (450 kW).[1]
- PW207E
- Maximum continuous power 572 shp (427 kW).[1] for use on the MD 902
- PW210
- Enhanced version of the PW200. Enhancements include; Lower fuel consumption, Dual Channel Full Authority Digital Engine Control (FADEC), Reduced environmental emissions and an Increase in power output ranging from 800 shp (600 kW) to 1,000 shp (750 kW)[2]
Applications
- AgustaWestland AW109
- AgustaWestland AW169
- Airbus Helicopters H160 (prototype only)
- Bell 429
- Boeing A160 Hummingbird
- Eurocopter EC 135
- MD Explorer
- Sikorsky S-76D
Specifications
Data from [3]
General characteristics
- Type: Turboshaft
- Length: 35.9 in (91.2 cm)
- Diameter: 19.7 in (50 cm)
- Dry weight: 237 lb (107.5 kg)
Components
- Compressor: Single-stage centrifugal
- Combustors: Annular
- Turbine: Single-stage high pressure turbine, single-stage low pressure turbine
Performance
- Maximum power output: 561 shp (418 kW)
- Specific fuel consumption: 0.542 lb/hp-hr
- Power-to-weight ratio: 2.4 hp/lb
References
- 1 2 3 4 5 6 7 8 9 10 "Type Certificate Data Sheet EA E.017 PW206 & PW207 series engines" (PDF). European Aviation Safety Agency. 28 July 2009. Retrieved 2009-12-26.
- ↑ "PW210". pwc.ca. Retrieved 11 March 2016.
- ↑ "Gas Turbine Engines. Aviation Week & Space Technology 2009 Source Book. pg. 126.". Aviation Week & Space Technology. 2009-01-26. Retrieved 2011-06-30.
External links
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