Supervisor:
Southwest Ordnance Industry Bureau
Organizer:
Chongqing Ordnance Industry Society
Chongqing University of Technology
Chongqing University of Technology
Study on general engine performance of variable geometry turbines and adjustable nozzle
| DOI: | 10.11809/bqzbgcxb2023.05.011 |
| Keywords: | variable geometry high pressure turbine; variable geometry low pressure turbine; variable nozzle area; performance study; gas turbine engine |
| Abstract: | In order to fully reveal the impact of variable geometry turbines and variable nozzle on engine performance, this paper establishes a component level simulation to model an engine. Then, the changes of the engine performance are systematically analyzed, and the overall performance parameters are quantitatively studied under the circumstances of respectively changing the flow area of the first stage guide vanes of the high pressure turbine, changing the flow area of the first stage guide vanes of the low pressure turbine and changing the nozzle outlet area. The research results show that when the flow capacity of the high pressure turbine or the low pressure turbine increases, both the total temperature and the total pressure of the nozzle inlet rise, and both the thrust and the specific fuel consumption also increase. When the flow capacity of the high pressure turbine increases by 10%, the thrust increases by only 1.69% and the specific fuel consumption increases by 2.52%; while the flow capacity of the low pressure turbine increases by 10%, the thrust increases by 13.16% and the specific fuel consumption also increases by 12.42%. When the nozzle outlet area expands, both the total temperature and the total pressure of the nozzle inlet decrease, and both the thrust and the specific fuel consumption reduce. When the nozzle outlet area expands by 10%, there is a significant 16.19% reduction in the thrust and a 4.02% reduction in the specific fuel consumption. |
| Issue: | Vol. 44 No. 5 (2023) |
| Published: | 2023-05-28 |
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