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Pratt & Whitney designed this engine for continuous operation at high Mach number flight with compressor inlet temperatures above 400 degrees C (750 degrees F). Development began about 1958, and production began in 1964.

The J58 had a single-shaft rotor design, with an 8.8:1 pressure ratio compressor, which incorporated a unique compressor bleed bypass at high Mach number. When opened, bypass valves bled air from the fourth stage, and six ducts routed it around the compressor rear stages, combustor, and turbine. The bleed air re-entered the turbine exhaust around the front of the afterburner where it was used for increased thrust and cooling. The main fuel control scheduled transition to bypass operation as a function of compressor inlet temperature and engine speed. For extreme high-altitude and high-speed environment operation, the engine required special fuel and oil.

Two J58 engines powered each Lockheed A-12 and YF-12 interceptor, and the SR-71 Blackbird reconnaissance and SR-71B trainer aircraft.

 Display Status

This object is on display in Nation of Speed at the National Air and Space Museum in Washington, DC.

Nation of Speed
Object Details
Date Circa 1965 Country of Origin United States of America Type PROPULSION-Turbines (Jet) Manufacturer Pratt & Whitney
 Physical Description Type: Turbojet, afterburner Thrust: 133,440 N (30,000 lb) Compressor: 8-stage axial Combustor: Cannular Turbine: 2-stage Weight: 2,948 kg (6,500 lb) Dimensions Overall: 8690 lb. (3941.8kg)
Other: 180 x 50in. (457.2 x 127cm)
Overall: 203.2 × 609.6cm (6 ft. 8 in. × 20 ft.)
 Materials Aluminum, Ceramic, Inconel, Plastic, Steel
 Inventory Number A19920006000 Credit Line Transferred from the U.S. Air Force, Norton AFB, California Data Source National Air and Space Museum Restrictions & Rights Usage conditions apply
For more information, visit the Smithsonians Terms of Use.