Westinghouse J32

J32
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Cut-away Westinghouse 9.5A/J32 turbojet engine on display at the Steven F. Udvar-Hazy Center
Type	Turbojet
National origin	United States
Manufacturer	Westinghouse Aviation Gas Turbine Division
First run	1944
Number built	44
Developed from	Westinghouse J30

The Westinghouse J32 was a small turbojet engine developed by the Westinghouse Aviation Gas Turbine Division in the mid-1940s.

Design and development

Development of the 9.5A (military designation J32-WE-2) began in late 1942, and Westinghouse delivered the first engine to the U.S. Navy in mid-1944. The Navy selected the 9.5A to power the Gorgon II-B and III-B air-to-air missiles, but these applications did not materialize."

An improved version, the 9.5B, powered the Martin TD2N-1 Gorgon high-speed target drone, which successfully flew in 1945. The engine's high cost and continuing development delays led to the cancellation of the TD2N-1 program in 1946. Westinghouse manufactured 24 of the 9.5A and 20 of the 9.5B engines. Despite their limited use, they constituted the first family of small turbojet engines successfully developed and produced in the United States.

Variants

J32

Military designation of the Westinghouse 9.5 turbojet engine

Westinghouse 9.5A

Company designation of the J32, denoting the diameter of the engine in inches

Westinghouse 9.5B

Improved version of the 9.5A

Applications

• Martin TD2N-1 Gorgon high-speed target drone

Engines on display

A cutaway Westinghouse 9.5A/J32 turbojet engine is on display at the Steven F. Udvar-Hazy Center in Washington D.C.

Specifications (9.5A)

Data from

General characteristics

• Type: Axial flow turbojet
• Length: 55.2 in (1,402.1 mm)
• Diameter: 9.5 in (241.3 mm)
• Dry weight: 9.5A 143 lb (64.9 kg), 9.5B 145 lb (65.8 kg)

Components

• Compressor: 6-stage axial
• Combustors: Annular stainless steel
• Turbine: Single-stage axial
• Fuel type: 100/130 gasoline
• Oil system: pressure spray at 65 psi (448.2 kPa)

Performance

• Maximum thrust: 9.5A 275 lbf (1.22 kN) at 36,000 rpm at sea level, 9.5B 260 lbf (1.16 kN) at 34,000 rpm at sea level
• Overall pressure ratio: 3:1
• Air mass flow: 5.25 lb (2.38 kg)/s at 28,000 rpm
• Turbine inlet temperature: 1,500 °F (816 °C)
• Specific fuel consumption: 1.7 lb/lbf/hr (173.3 kg/kN/h)
• Thrust-to-weight ratio: 1.92 lbf/lb (0.0189 kN/kg)
• Normal thrust, static: 9.5A 175 lbf (0.78 kN) at 29,800 rpm at sea level, 9.5B 260 lbf (1.16 kN) at 34,000 rpm at sea level
• Military thrust, flight: 215 lbf (0.96 kN) at 36,000 rpm at altitude
• Normal thrust, flight: 160 lbf (0.71 kN) at 29,800 rpm at altitude

References

• This article contains material that originally came from the placard at the Steven F. Udvar-Hazy Center.