Pratt & Whitney JT9D: Difference between revisions
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Revision as of 01:19, 15 June 2011
| JT9D | |
|---|---|
| |
| The internal structure of the JT9D. | |
| Type | Turbofan |
| Manufacturer | Pratt & Whitney |
| First run | December 1966 |
| Major applications | Boeing 747 Boeing 767 Airbus A310 McDonnell Douglas DC-10 |
The Pratt & Whitney JT9D engine was the first high bypass ratio jet engine to power a wide-body aircraft. Its initial application was the Boeing 747-100, the original "Jumbo Jet". It was the company's first high-bypass-ratio turbofan and also the first of today's generation of large commercial turbofan engines to be produced.[1]
Design and development
The JT9D was developed as part of the design phase of the C-5 Galaxy, a contract was awarded to Pratt & Whitney to study the type of large engine needed but the production contract was eventually awarded to General Electric and their TF39 turbofan. The JT9D was however chosen by Boeing to power the 747 with that aircraft's first flight taking place on 9 February 1969. Flight testing of the engine had begun in June 1968, using a Boeing B-52E as a testbed.
The JT9D-3 which entered service in 1970 was constructed using titanium and nickel alloys. The engine featured a single stage fan, a three stage low pressure compressor and an eleven stage high pressure compressor coupled to a two stage high pressure turbine and four stage low pressure turbine. This version of the JT9D weighed 8,608 lb (3,905 kg) and produced 43,500 lbf (193,000 N) thrust. Production ceased in 1990.
JT9D engines powering USAF E-4A airborne command posts are designated Pratt & Whitney F105.
Pratt & Whitney's designated successor to the JT9D family is the PW4000, which features fewer parts, greater reliability, and lower base selling price.
Applications
Specifications
| JT9D Engine Family | ||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| JT9D-3A | JT9D-7 | JT9D-20 | JT9D-7Q/7Q3 | JT9D-59A/70A | JT9D-7R4D/D1 | JT9D-7R4G2 | JT9D-7R4H1 | |||||||
| Static Thrust (lbf) | 45800 | 47900 | 49400 | 53000 | 53000 | 48000 | 54750 | 56000 | ||||||
| Basic Engine Weight (lb) | 8608 | 8850 | 8450 | 9295 | 9155 | 8905 | 8935 | 8885 | ||||||
| Length (in) | 128.2 | 128.2 | 128.2 | 132.1 | 132.2 | 132.7 | 132.7 | 132.7 | ||||||
| Fan Diameter (in) | 92.3 | 92.3 | 92.3 | 93.6 | 93.6 | 93.4 | 93.4 | 93.4 | ||||||
| Used in | Boeing 747-100 | Boeing 747/Boeing 767 | McDonnell Douglas DC-10/Boeing 747 | Boeing 747 | McDonnell Douglas DC-10/Boeing 747 | Boeing 767/Airbus A310 | Boeing 747 | Airbus A300 | ||||||
See also
Related development
Comparable engines
Related lists
References
Notes
- ^ Gunston 1989, p.126.
Bibliography
- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
