Kowasaki TF2: Difference between revisions
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{{wip}} | {{wip}} | ||
{|{{Infobox | {|{{Infobox aircraft begin | ||
|name= TF2 | |name= TF2 | ||
|image= File:Rd-93.jpg | |image= File:Rd-93.jpg | ||
|caption= | |caption= A TF2-10 engine on display. | ||
}}{{Infobox | }}{{Infobox aircraft engine | ||
|type= | |type= {{wpl|Turbofan}} | ||
|manufacturer= [[Kowasaki Heavy Industries]] | |manufacturer= [[Kowasaki Heavy Industries]] | ||
|national origin= [[Chilokver]] | |national origin= [[Chilokver]] | ||
|first run= | |first run= | ||
|major applications= [[Nakajima CF-05 Goshawk]] | |major applications= [[Shangtian F-8 Eagle]]<br>[[Nakajima CF-05 Goshawk]] | ||
|produced= | |produced= | ||
|number built= | |number built= | ||
| Line 20: | Line 20: | ||
The '''Kowasaki TF2''' is a series of afterburning {{wpl|Turbofan|turbofan}} jet engines developed by [[Kowasaki Heavy Industries]]. | The '''Kowasaki TF2''' is a series of afterburning {{wpl|Turbofan|turbofan}} jet engines developed by [[Kowasaki Heavy Industries]]. | ||
==Variants== | ==Variants== | ||
;TF2-10: Original variant of the TF2 developed for the [[Shangtian F-8 Eagle]]. | |||
==Applications== | ==Applications== | ||
* [[Shangtian F-8 Eagle]] | |||
* [[Nakajima CF-05 Goshawk]] | |||
==Specifications (TF2-20)== | ==Specifications (TF2-20)== | ||
Latest revision as of 04:37, 6 October 2019
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| TF2 | |
|---|---|
| |
| A TF2-10 engine on display. | |
| Type | Turbofan |
| National origin | Chilokver |
| Manufacturer | Kowasaki Heavy Industries |
| Major applications | Shangtian F-8 Eagle Nakajima CF-05 Goshawk |
The Kowasaki TF2 is a series of afterburning turbofan jet engines developed by Kowasaki Heavy Industries.
Variants
- TF2-10
- Original variant of the TF2 developed for the Shangtian F-8 Eagle.
Applications
Specifications (TF2-20)
General characteristics
- Type: Afterburning turbofan
- Length: 4,145 mm (163.19 in)
- Diameter: 1,020 mm (40.16 in)
- Dry weight: 1,135 kilograms (2,502 lb)
Components
- Compressor: Axial compressor with 4 low-pressure and 8 high-pressure stages
- Combustors: Annular
- Turbine: 1 low-pressure and 1 high-pressure stage
Performance
- Maximum thrust: 56.75 kilonewtons (12,760 lbf) dry; 86.37 kilonewtons (19,420 lbf) with afterburner
- Overall pressure ratio: 24:1
- Bypass ratio: 0.57:1
- Turbine inlet temperature: 1,377 °C (2,511 °F)
- Thrust-to-weight ratio: 5.1 (dry), 7.8 (afterburning)