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Pratt & Whitney Canada PW210S)
| PW200 | |
|---|---|
| Type | Turboshaft |
| National origin | Canada |
| Manufacturer | Pratt & Whitney Canada |
| Major applications |
AgustaWestland AW109 Bell 429 Eurocopter EC135 MD Explorer Sikorsky S-76D |
| Number built | >5,400 [1] |
The Pratt & Whitney Canada PW200 is a family of turboshaft engines developed specifically for helicopter applications. It entered service in the 1990s.
Variants
- PW205B
- First run 1987. Flown in twin-engine MBB BO105 for demonstration only. [2]
- PW206A
- Maximum continuous power 550 shp (410 kW) [3] for use on the MD Explorer
- PW206B
- Maximum continuous power 431 shp (321 kW), [3] for use on the Eurocopter EC135
- PW206B2
- Maximum continuous power 431 shp (321 kW). [3]
- PW206C
- Maximum continuous power 561 shp (418 kW), [3] for use on the Agusta A109 Power
- PW206E
- Maximum continuous power 572 shp (427 kW). [3] for use on the MD Explorer
- PW207C
- Maximum continuous power 572 shp (427 kW). [3]
- PW207D
- Maximum continuous power 572 shp (427 kW). [3]
- PW207D1
- Variant of the PW207 with increased mechanical power, maximum continuous power 610 shp (450 kW). [3]
- PW207D2
- Variant of the PW207D1 with a fuel heater installed, maximum continuous power 610 shp (450 kW). [3]
- PW207E
- Maximum continuous power 572 shp (427 kW). [3] for use on the MD 902
- PW209T
- Maximum continuous power 800 shp (600 kW). "Twin-pack" First run 1985, cancelled 1987. Intended for Bell TwinRanger [4]
- 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) [5]
Applications
- AgustaWestland AW109
- AgustaWestland AW169
- Airbus Helicopters H160 (prototype only)
- Bell 360 Invictus (planned)
- Bell 429 GlobalRanger
- Boeing A160 Hummingbird
- Eurocopter EC135
- MD Helicopters MD Explorer
- Sikorsky S-76D
Specifications
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. PW210: Two-stage mixed flow and centrifugal
- Combustors: Annular
- Turbine: Single-stage high pressure turbine, single-stage power turbine. PW210: Two-stage power 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
- ^ "PW200 - Pratt & Whitney".
- ^ "Power The Pratt & Whitney Canada Story" Sullivan and Milberry, CANAV Books 1989, ISBN 0-921022-01-8, p.300
- ^ a b c d e f g h i j "Type Certificate Data Sheet EA E.017 PW206 & PW207 series engines" (PDF). European Aviation Safety Agency. 28 July 2009. Archived from the original (PDF) on 23 December 2009. Retrieved 2009-12-26.
-
^
"Archived copy". Archived from
the original on 2018-09-26. Retrieved 2016-12-21.
{{ cite web}}: CS1 maint: archived copy as title ( link) - ^ "PW210". pwc.ca. Retrieved 11 March 2021.
- ^ "Gas Turbine Engines. Aviation Week & Space Technology 2009 Source Book. pg. 126". Aviation Week & Space Technology. 2009-01-26. Retrieved 2011-06-30.[ permanent dead link]
- ^ "EASA TYPE-CERTIFICATE DATA SHEET" (PDF). EASA. Retrieved 17 March 2019.