Wright J65

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J65
Wright J65.jpg
Sectioned Wright J65
Type Turbojet
Manufacturer Curtiss-Wright
First run 1 October 1948
Major applications Douglas A-4 Skyhawk
Grumman F-11 Tiger
Martin B-57 Canberra
Republic F-84F Thunderstreak
Developed from Armstrong Siddeley Sapphire

The Wright J65 was an axial-flow turbojet engine produced by Curtiss-Wright under license from Armstrong Siddeley. A development of the Sapphire, the J65 powered a number of US designs.

Design and development[edit]

Curtiss-Wright purchased a license for the Sapphire in 1950, with plans to have the production lines running in 1951. However a series of delays due to design changes by Curtiss-Wright, such as substituting the Sapphire's machined midsection solid forged diffuser frame with a fabricated one of welded nodular iron,[1] led to its service introduction slipping two years. The fabricated assembly, a more practicable production job at about one fifth the cost was subsequently adopted for the Sapphire.[2] Another design change which was also evaluated for the Sapphire, but not adopted, addressed compressor blade stalling (and subsequent fatigue) at low engine RPM. Ramps were installed at the entry to the compressor. They were raised at low RPM to prevent stalling.[3][4]

By service introduction the Pratt & Whitney J57 was on the market and took many of the J65's potential sales. Nevertheless, along with the Martin B-57 Canberra, its original application, the J65 went on to power versions of the North American FJ Fury, Douglas A-4 Skyhawk, Republic F-84F Thunderstreak, and the two Lockheed XF-104 Starfighter prototypes. Problems Grumman had with the engine in the F11F Tiger, particularly below-spec after-burning thrust, caused them to specify the J79 for the Grumman F11F-1F Super Tiger.[5]

Wright T49[edit]

A 6,500–10,380 shp (4,850–7,740 kW) turboprop version of the J65 (Sapphire) was developed by Curtiss-Wright as the Wright T49, and a commercial derivative, the Wright TP51A2 was also designed. The T49 first ran in December 1952 at 8,000 shp (6,000 kW), followed by flight testing in a Boeing XB-47D test bed from 26 August 1955. By this time however, the market for the engine had vanished.[6]

Applications[edit]

Specifications (J65-B)[edit]

General characteristics

  • Type: Turbojet
  • Length: ~122in (~3098 mm)
  • Diameter: 37.52in (953 mm)
  • Dry weight: 2776lb (1259 kg)

Components

Performance

See also[edit]

Related development
Comparable engines
Related lists

References[edit]

  1. ^ "World Encyclopedia of Aero Engines - 5th edition" by Bill Gunston, Sutton Publishing, 2006, p.249
  2. ^ https://www.flightglobal.com/pdfarchive/view/1956/1956%20-%200020.html
  3. ^ https://www.flightglobal.com/pdfarchive/view/1956/1956%20-%200022.html
  4. ^ ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19930088525.pdf
  5. ^ "Grumman's Mach-2 International F11F-1F Supertiger" Corwin Meyer, Naval Fighters Number Forty-Four, Steve Ginter 1998, ISBN 0-942612-44-2, p.1
  6. ^ "World Encyclopedia of Aero Engines - 5th edition" by Bill Gunston, Sutton Publishing, 2006, p.249
  • Gunston, Bill (2006). World Encyclopedia of Aero Engines, 5th Edition. Phoenix Mill, Gloucestershire, England, UK: Sutton Publishing Limited. ISBN 0-7509-4479-X. 
  • Kay, Anthony L. (2007). Turbojet History and Development 1930-1960. 2 (1st ed.). Ramsbury: The Crowood Press. ISBN 978-1861269393. 

External links[edit]