# Pratt & Whitney Canada PW300

The Pratt & Whitney Canada PW300 series is a family of turbofan jet engines developed by Pratt & Whitney Canada specifically for business jet applications.

## Design and development

The PW 300 series has been developed in partnership with MTU who are responsible for the low pressure turbine.
The first variant, the PW305A, has the following configuration and was designed with a core flexible enough for engines with take-off thrusts from 20 kN to 31 kN (4,500 to 7,000 lb): a single-stage fan driven by a three-stage low pressure turbine, supercharging a four-stage axial/single-stage centrifugal high-pressure compressor, driven by a two-stage high-pressure turbine. An annular combustor is used. There is no forced mixing before the bypass and core streams leave the engine through a common nozzle. The engine is controlled with a dual channel Full Authority Digital Engine Control (FADEC) system.
The PW307A is a new centre-line engine developed specifically for a tri-jet application on the Dassault Falcon 7X. The PW307 was certified by Transport Canada in March 2005.
The PW308A has been chosen to power the Scaled Composites White Knight Two, the launch aircraft for Virgin Galactic's SpaceShipTwo.
Unscheduled interventions went from 85% in 2015 to 20% in 2017, driving up the PW307 availability thanks to Pratt's digital platform, and engine dispatch reliability is at 99.4% for the Falcon 7X/8X powered by the PW307.

## Variants
### PW305A

    20.81 kN (4,680 lb$_f$) variant used on the Bombardier Learjet 60.

### PW305B

    23.41 kN (5,260 lb$_f$) variant used on the Hawker 1000.

### PW306A

    25.36 kN (5,700 lb$_f$) variant used on the IAI Galaxy & Gulfstream G200.

### PW306B

    Variant used on the Dornier 328JET.

### PW306C

    25.67 kN (5,770 lb$_f$) variant used on the Cessna Citation Sovereign.

### PW306D

    26.28 kN (5,910 lb$_f$) variant used on the Cessna Citation Sovereign +.

### PW306D1

    25.6 kN (5,800 lb$_f$) variant used on the Cessna Citation Latitude.

### PW307A

    28.49 kN (6,400 lb$_f$) variant used on the Dassault Falcon 7X. Originally 27.1 kN (6,100 lb$_f$) growth version of the PW306, smaller than the PW308, featuring swept-blade fan, increased core airflow, low NOx emissions combustor, increased turbine capacity and a more efficient exhaust mixer; integrated propulsion system including Macchi/Hurel Dubois nacelle and thrust-reverser; certification scheduled for the end of 2004.

### PW307B

    Variant used on the Bombardier Learjet 85.

### PW307D

    Variant used on the Dassault Falcon 8X.

### PW308A

    30.69 kN (6,900 lb$_f$) variant used on the Hawker 4000 & Scaled Composites White Knight Two.

### PW308C

    31.14 kN (7,000 lb$_f$) variant used on the Dassault Falcon 2000EX/DX/LX.

## Applications

* Cessna Citation Latitude
* Cessna Citation Sovereign
* Dassault Falcon 2000EX/DX/LX
* Dassault Falcon 7X
* Fairchild Dornier 328JET
* Fairchild Dornier 428JET
* Gulfstream G200
* Hawker 1000
* Hawker 4000
* Learjet 60
* Learjet 85
* Scaled Composites White Knight Two

## Specifications (PW306B)

Data from Jane's all the World's Aircraft 1993–94

#### General characteristics

* Type: Turbofan
* Length: 2,062 mm (81.2 in)
* Diameter: 970.3 mm (38.20 in)
* Dry weight: 450 kg (990 lb) installed

#### Components

* Compressor: 1-stage fan, 4-stage axial with 1-stage centrifugal high pressure compressor
* Combustors: Annular
* Turbine: 2 stage high pressure, 3 stage low pressure turbines.
* Fuel type: Aviation Kerosene such as JP-1, JP-4, JP-5 or CPW-204
* Oil system: Pressure spray integral system with gear pump and scavenge, capacity 2.11 US gal (1.76 imp gal; 8.0 L)

#### Performance

* Maximum thrust: 23.24 kN (5,220 lb$_f$) for take-off or flat-rated at 21.13 kN (4,750 lb$_f$) up to 25 °C (77 °F)
* Cruise thrust: 5.03 kN (1,130 lb$_f$) at M0.8 at 12,200 m (40,000 ft)
* Overall pressure ratio: Core pressure ratio: 15:1
* Bypass ratio: 4.5:1
* Specific fuel consumption: 41.5 kg/kN/h (0.407 lb/lbf/h) at take-off
* Cruise s.f.c.: 69.9 kg/kN/h (0.685 lb/lbf/h)
* Thrust-to-weight ratio: 5.26 at take-off power