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Westinghouse J30 / 19 / 19B / 19XB

 

West-19A
Westinghouse 19A

 

Design of 19A Yankee was begun on 10 August 1942. It had six axial stage compressor, a twenty four cannular combustion chamber and a single stage turbine.

 

On 19 March 1943, the first run was made. The static thrust developed being 515 kg (1,135 lb). On 21 January 1944 the second prototype was flown for the first time, under a Vought FG-1 Corsair. It was developed into the smaller J32, and the Westinghouse J34, an enlarged version which produced 3,000 pounds of thrust.

 

Six 19A were built all together. It initially gave 1,200 pounds of thrust but improved to 1,600 in production versions.

 

The 19B was to have a static thrust of 613 Kg (1350 lb) and be used as the main propulsion engine for an aircraft, rather than just a booster. The layout of the compressor and turbine was similar to the 19A, but 4 extra stages were added to the compressor to give ten in all. The previous cannular combustion chamber was replaced by an annular one.

 

First flight was made on 28 September 1944, using a JM-1 Marauder as a test-bed.

 

The McDonnell XFD-1 Phamtom powered by two 19Bs made its first flight on January 26, 1945. The Northrop XP-79B was also powered by two 19Bs, but crashed on its first flight on September 12, 1945.

 

A total of 28 19B were ordered.


West-J30

 

Westinghouse submitted to the Navy a proposal for improving the performance and decreasing the weight of the 19B. This reconfigured engine was designated 19XB. The 1,600 lb thrust of the 19XB was achieved primarily by adding 4 additionnal axial-flow compressor stages.

 

The 19XB was used in the Gruman WTB3F-1, Douglas XB-42A (as auxiliary engines) and the Northrop X-4. The primary application for the 19XB engine was the McDonnell FH-1 Phantom.

 

A total of 261 19XB engines were made.

 

West-19

 

Westing-J30-nd
Inside/Rear view of 19XB2B Inlet
specific model: J30-P-20
Engine Spec Number: WAGT-19XB2B-102D
Accepted 12-23-47
(Courtesy Doug Colosio)

 

Variants:
19A
Prototypes and initial production

19B
Increased mass flow version delivering 1,400 lbf (6.23 kN) at 18,000 rpm at sea level

J30-WE-20
production engines delivering 1,600 lbf (7.1 kN) thrust

 

Applications:
Convair XF-92
McDonnell FH Phantom
Northrop XP-79
Northrop X-4 Bantam

 

Specifications:
Westinghouse 19A
Type: Axial flow turbojet
Length: 100 in (2,540.0 mm)
Diameter: 19 in (482.6 mm)
Dry weight: 830 lb (376.5 kg)
Compressor: 6-stage axial
Combustors: Annular stainless steel
Turbine: Single-stage axial
Fuel type: 100/130 gasoline
Oil system: pressure spray at 40 psi (275.8 kPa) dry sump, 60 S.U. secs (10.2 cs) (AN-0-6A) grade oil
Maximum thrust: 1,360 lbf (6.05 kN) at 18,000 rpm at sea level
Overall pressure ratio: 3:1
Turbine inlet temperature: 1,500 °F (816 °C)
Specific fuel consumption: 1.35 lb/lbf/hr (137.6 kg/kN/hr)
Thrust-to-weight ratio: 1.639 lbf/lb (0.016 kN/kg)
Normal thrust, static: 1,160 lbf (5.16 kN) at 18,000 rpm at sea level
Military thrust, flight: 660 lbf (2.94 kN) at 17,200 rpm at altitude
Normal thrust, flight: 570 lbf (2.54 kN) at 16,260 rpm at altitude

 

Westinghouse 19B
Type: Axial flow turbojet
Length: 104.5 in (2,654.3 mm)
Diameter: 19 in (482.6 mm)
Dry weight: 809 lb (367.0 kg)
Compressor: 6-stage axial
Combustors: Annular stainless steel
Turbine: Single-stage axial
Fuel type: 100/130 gasoline
Oil system: pressure spray at 40 psi (275.8 kPa) dry sump, 60 S.U. secs (10.2 cs) (AN-0-6A) grade oil
Maximum thrust: 1,400 lbf (6.23 kN) at 18,000 rpm at sea level
Overall pressure ratio: 3:1
Turbine inlet temperature: 1,500 °F (816 °C)
Specific fuel consumption: 1.28 lb/lbf/hr (130.48 kg/kN/hr)
Thrust-to-weight ratio: 1.724 lbf/lb (0.0169 kN/kg)
Normal thrust, static: 1,170 lbf (5.20 kN) at 17,000 rpm at sea level
Military thrust, flight: 525 lbf (2.34 kN) at 18,000 rpm at altitude
Normal thrust, flight: 465 lbf (2.07 kN) at 17,000 rpm at altitude

 

 

 

 

 

 


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