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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.

PW206A

Maximum continuous power 550 shp (410 kW) for use on the MD Explorer

PW206B

Maximum continuous power 431 shp (321 kW), for use on the Eurocopter EC135

PW206B2

Maximum continuous power 431 shp (321 kW).

PW206C

Maximum continuous power 561 shp (418 kW), for use on the Agusta A109 Power

PW206E

Maximum continuous power 572 shp (427 kW). for use on the MD Explorer

PW207C

Maximum continuous power 572 shp (427 kW).

PW207D

Maximum continuous power 572 shp (427 kW).

PW207D1

Variant of the PW207 with increased mechanical power, maximum continuous power 610 shp (450 kW).

PW207D2

Variant of the PW207D1 with a fuel heater installed, maximum continuous power 610 shp (450 kW).

PW207E

Maximum continuous power 572 shp (427 kW). 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

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)

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

Data from

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 (3.9 kW/kg)

References

1. "PW200 - Pratt & Whitney".
2. "Power The Pratt & Whitney Canada Story" Sullivan and Milberry, CANAV Books 1989, ISBN 0-921022-01-8, p.300
3. ^ "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.
4. "Archived copy". Archived from the original on 2018-09-26. Retrieved 2016-12-21.{{cite web}}: CS1 maint: archived copy as title (link)
5. "PW210". pwc.ca. Retrieved 11 March 2021.
6. "Gas Turbine Engines. Aviation Week & Space Technology 2009 Source Book. pg. 126". Aviation Week & Space Technology. 2009-01-26. Retrieved 2011-06-30.
7. "EASA TYPE-CERTIFICATE DATA SHEET" (PDF). EASA. Archived from the original (PDF) on 28 November 2020. Retrieved 17 March 2019.

External links

• Pratt & Whitney Canada PW200 webpage
• Pratt & Whitney Canada PW210 webpage

• 1980s turboshaft engines
• Pratt & Whitney Canada aircraft engines