Pratt & Whitney Canada JT15D
| JT15D | |
|---|---|
.jpg) Aerocardal JT15D | |
| Type | Turbofan |
| National origin | Canada |
| Manufacturer | Pratt & Whitney Canada |
| First run | 1967 |
| Major applications | Cessna Citation I Cessna Citation V Hawker 400 SIAI Marchetti S.211 |
| Number built | >6,000 |
The Pratt & Whitney Canada JT15D is a small turbofan engine built by Pratt & Whitney Canada. It was introduced in 1971 at 2,200 lbf (9,800 N) thrust, and has since undergone a series of upgrades to just over 3,000 lbf (13 kN) thrust in the latest versions. It is the primary powerplant for a wide variety of smaller jet aircraft, notably business jets.
Design and development
[edit]The JT15D was first run in 1967. Its use of a centrifugal compressor as the high-pressure stage in a turbofan engine was followed in 1970 by the Garrett TFE731.[1] The fan for the original JT15D-1 was aerodynamically scaled to 75 lb/sec using the much larger Pratt & Whitney JT9D fan, first used on the Boeing 747.[2]
About 70% of the air passing through the fan goes down the bypass duct. The JT15D-4 and later variants use a "booster" axial stage behind the fan which runs at the same speed as the fan and directs the remaining 30% of the air into the high-pressure compressor, after which it passes into a reverse-flow annular combustor. The hot gases flow through a high-pressure turbine that drives the centrifugal compressor, and a low-pressure turbine that drives the fan and booster.
The engine was first run in August 1967 before being test flown on an Avro Canada CF-100 Canuck in an underslung external test pod.[3] In 1975 a unique over-wing installation in place of Pratt & Whitney Canada PT6 turboprops was fitted to a Beechcraft Super King Air and flown for 93 hours to investigate the use of turbofan engines on that airframe.[4][5]
Variants
[edit].jpg)
- JT15D-1
- The first model was introduced to power the Cessna Citation I, then known as the Fanjet 500. Deliveries started in 1972, and eventually on 1,417 -1s were delivered.
- JT15D-1A
- JT15D-1B
- JT15D-4
- Introduced in 1973, improving thrust to 2,500 lbf (11,000 N). The -4 was the primary engine for the Cessna Citation II, and went on to find use on the Mitsubishi Diamond 1A, Aerospatiale Corvette and SIAI-Marchetti S.211. Eventually 2,195 engines of the -4 series were delivered.
- JT15D-4A
- JT15D-4B
- JT15D-4C
- JT15D-4D
- JT15D-5
- Certified in 1983. The first versions delivered 2,900 lbf (13,000 N) and were used on the Beechjet 400A and Cessna T-47A. Several minor versions were introduced, the -5A for the Cessna Citation V, while the -5B powered the Beechcraft T-1A Jayhawk, the -5C the DASA Ranger 2000 and S-211A.
- JT15D-5A
- JT15D-5B
- JT15D-5C
- JT15D-5D
- Certified in 1993, increased thrust again, this time to 3,045 lbf (13,540 N). The -5D is used on the Cessna UC-35A and Cessna Citation Ultra.
- JT15D-5F
Applications
[edit].jpg)
- Aérospatiale Corvette
- Alenia Aermacchi M-311
- Ball-Bartoe Jetwing
- Boeing Bird of Prey
- Beechcraft Beechjet 400
- Cessna Citation I
- Cessna Citation II
- Cessna Citation V/Ultra
- EADS Barracuda
- Hawker 400
- Honda MH02
- Mitsubishi MU-300 Diamond
- Northrop Grumman X-47A Pegasus
- Raytheon T-1 Jayhawk
- Rockwell Ranger 2000
- Scaled Composites 401
- Scaled Composites ARES
- SIAI-Marchetti S.211/Aermacchi S-211
- Sport Jet II
- Stratos 716X
Specifications (JT15D-5D)
[edit]General characteristics
- Type: Turbofan
- Length: 60.3 in (1,530 mm)
- Diameter: 27 in (690 mm)
- Dry weight: 630 lb (290 kg)
Components
- Compressor: Axial flow LP, centrifugal flow HP
- Fuel type: Jet A/A1
Performance
- Maximum thrust: 3,050 lbf (1,380 kgf; 13.6 kN)
- Specific fuel consumption: 0.562 lb/(lbf⋅h) (15.9 g/(kN⋅s)) at maximum thrust; 0.552 lb/(lbf⋅h) (15.6 g/(kN⋅s)) at cruise (typical)
- Thrust-to-weight ratio: ≈ 4.58
| Engine | Takeoff thrust (kN) | Continuous thrust (kN) | Length (mm) | Fan Diameter(mm) | Diameter.(mm) | Dry weight (kg) | Bypass ratio |
|---|---|---|---|---|---|---|---|
| JT15D-1 | 9.8 | 9.3 | 1506 | 691 | 223.5 | 3.3 | |
| JT15D-4 | 11.12 | 10.56 | 1600 | 686 | 253 | 2.6 | |
| JT15D-4C | 11.12 | 10.56 | 1600 | 686 | 261 | 2.6 | |
| JT15D-5 | 12.92 | 1600 | 287 | 2 | |||
| JT15D-5A | 12.92 | 1600 | 287 | 2 | |||
| JT15D-5B | 12.92 | 1600 | 292 | 2 | |||
| JT15D-5C | 14.21 | 1600 | 302 | 2 | |||
| JT15D-5D | 13.56 | 1531 | 520 | 686 | 292.6 | 3.3 | |
| JT15D-5F | 12.92 | 1600 | 288 | 2 |
References
[edit]Notes
[edit]- ↑ The Development Of Jet And Turbine Aero Engines 4th Edition,Bill Gunston 2006,ISBN 0 7509 4477 3,p.185.
- ↑ Gunston 1989, p.131.
- ↑ "On Test at Longueuil". Flight International: 263. 13 February 1969.
- ↑ Philips; Phillips, Edward H. (1992). Beechcraft, pursuit of perfection : A history of beechcraft airplanes. Flying Books. ISBN 978-0-911139-11-2.
- ↑ "Bygone Beechcrafts – Part Two".
Bibliography
[edit]- Gunston, Bill. World Encyclopedia of Aero Engines. Cambridge, England. Patrick Stephens Limited, 1989. ISBN 1-85260-163-9
External links
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