The influence of cycle parameters on inter-turbine burner turbofan engine performance
A performance simulation program for inter-turbine burner (ITB) turbofan engine was made with the variable specific heat components method, the influence of cycle parameters such as fan pressure ratio, compressor pressure ratio, bypass ratio, turbine inlet temperature on engine performance was analy...
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| Veröffentlicht in: | Danjian yu Zhidao Xuebao / Journal of Projectiles, Rockets, Missiles and Guidance Rockets, Missiles and Guidance, 2009-10, Vol.29 (5), p.152-154 |
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| container_issue | 5 |
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| container_title | Danjian yu Zhidao Xuebao / Journal of Projectiles, Rockets, Missiles and Guidance |
| container_volume | 29 |
| creator | Luo, Guangqi Song, Wenyan Song, Diyuan |
| description | A performance simulation program for inter-turbine burner (ITB) turbofan engine was made with the variable specific heat components method, the influence of cycle parameters such as fan pressure ratio, compressor pressure ratio, bypass ratio, turbine inlet temperature on engine performance was analyzed comparatively. The result shows that the specific thrust performance of ITB engine is better; the specific fuel consumption curve is toning down with the varied cycle parameters mentioned above, the range which cycle parameters can be selected is wider than that of conventional engine. |
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The result shows that the specific thrust performance of ITB engine is better; the specific fuel consumption curve is toning down with the varied cycle parameters mentioned above, the range which cycle parameters can be selected is wider than that of conventional engine.</description><identifier>ISSN: 1673-9728</identifier><language>chi</language><subject>Bypass ratio ; Compressors ; Engines ; Fuel consumption ; Inlet temperature ; Missiles ; Pressure ratio ; Projectiles ; Rockets ; Simulation ; Spacecraft components ; Specific heat ; Thrust ; Toning ; Turbines ; Turbofan engines</subject><ispartof>Danjian yu Zhidao Xuebao / Journal of Projectiles, Rockets, Missiles and Guidance, 2009-10, Vol.29 (5), p.152-154</ispartof><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784</link.rule.ids></links><search><creatorcontrib>Luo, Guangqi</creatorcontrib><creatorcontrib>Song, Wenyan</creatorcontrib><creatorcontrib>Song, Diyuan</creatorcontrib><title>The influence of cycle parameters on inter-turbine burner turbofan engine performance</title><title>Danjian yu Zhidao Xuebao / Journal of Projectiles, Rockets, Missiles and Guidance</title><description>A performance simulation program for inter-turbine burner (ITB) turbofan engine was made with the variable specific heat components method, the influence of cycle parameters such as fan pressure ratio, compressor pressure ratio, bypass ratio, turbine inlet temperature on engine performance was analyzed comparatively. 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The result shows that the specific thrust performance of ITB engine is better; the specific fuel consumption curve is toning down with the varied cycle parameters mentioned above, the range which cycle parameters can be selected is wider than that of conventional engine.</abstract><tpages>3</tpages></addata></record> |
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| identifier | ISSN: 1673-9728 |
| ispartof | Danjian yu Zhidao Xuebao / Journal of Projectiles, Rockets, Missiles and Guidance, 2009-10, Vol.29 (5), p.152-154 |
| issn | 1673-9728 |
| language | chi |
| recordid | cdi_proquest_miscellaneous_36287928 |
| source | Alma/SFX Local Collection |
| subjects | Bypass ratio Compressors Engines Fuel consumption Inlet temperature Missiles Pressure ratio Projectiles Rockets Simulation Spacecraft components Specific heat Thrust Toning Turbines Turbofan engines |
| title | The influence of cycle parameters on inter-turbine burner turbofan engine performance |
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