Method for adjusting and designing outlet area of engine jet pipe based on installation performance

A technology of engine nozzle and outlet area, which is applied in the field of aircraft, can solve problems such as limiting the installation performance of the propulsion system, and achieve the effect of improving the installation thrust

Inactive Publication Date: 2012-10-31
中航空天发动机研究院有限公司
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Problems solved by technology

However, the outlet area of ​​the nozzle has a great influence on the body resistance after flight. Therefore, when designing the adjustment plan for the out...

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  • Method for adjusting and designing outlet area of engine jet pipe based on installation performance
  • Method for adjusting and designing outlet area of engine jet pipe based on installation performance

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Embodiment 1

[0014] This embodiment provides a design method for adjusting the nozzle outlet area of ​​an engine based on installation performance, which is characterized in that: the design method for adjusting the outlet area of ​​an engine nozzle based on installation performance is:

[0015] According to the engine main adjustment plan, limit value, flight altitude and Mach number, use engine zero-dimensional calculation software (such as turbotrans, etc.) to calculate the engine cross-section parameters and adjustable cross-section area. At this time, 101% of the throat area of ​​the nozzle is taken as the minimum value. Taking 250% of the throat area as the maximum value, the exit area of ​​the nozzle series is divided into 13 parts, and the flow field inside and outside the nozzle is calculated according to the structural size of the engine nozzle, the throat area, and the area of ​​the nozzle exit series. Three-dimensional or two-dimensional model, the flow field inside and outside ...

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Abstract

The invention discloses a method for adjusting and designing the outlet area of an engine jet pipe based on installation performance. Engine zero dimension calculation software is adopted to calculate section parameters and adjustable sectional area of an engine according to a main adjustment plan, limit values, a flight altitude and a mach number of the engine, wherein 101% of the current throat area of the jet pipe is taken as a minimum value, and 250% of the throat area is taken as a maximum value; the series outlet area of the jet pipe is divided equally into 13 parts; a jet pipe flow field at various outlet area conditions is calculated by flow field calculation software; non-installation thrust and afterbody drag of the engine jet pipe are after-processed and calculated by the flow field calculation software; a maximum value of the sum of the non-installation thrust and the afterbody drag is selected; and the outlet area, which corresponds to the maximum value, of the jet pipe is the optimum outlet area of the jet pipe at the condition. The method has the advantages that the installation thrust of the engine can be effectively improved on the premise that the structure of the engine jet pipe and the working state of the engine are not changed.

Description

technical field [0001] The invention relates to the technical field of aircraft with an actively adjustable engine nozzle outlet area, in particular to a design method for adjusting the engine nozzle outlet area based on installation performance. Background technique [0002] Existing aero-engine nozzle outlet area adjustment plan design only considers the non-installation performance of the engine, and now advanced fighter jets require long-term supersonic cruise without afterburner. As the cruise speed increases, the flight resistance increases. The main components that analyze the resistance of the aircraft are: wings, fuselage, empennage, canopy and landing gear, among which the resistance of the rear body of the fuselage accounts for 38-50% of the total aircraft resistance. However, the nozzle outlet area has a great influence on the after-flight body resistance. Therefore, only considering the non-installation thrust has limited the installation performance of the prop...

Claims

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Application Information

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IPC IPC(8): G06F17/50F02K1/11
Inventor 谢业平邱明星施磊赵肃芮长胜刘月玲
Owner 中航空天发动机研究院有限公司
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