串联式TBCC进气道模态转换模拟器设计及其特性分析

doi:10.7527/S1000-6893.2016.0103

Abstract

Abstract:

In order to simulate the smooth mode transition of turbine based combined cycle (TBCC) propulsion system, the mode transition simulator for tandem type TBCC inlet is redesigned based on the experiences learned from the high speed wind tunnel test. The linear and asymmetric methods are then used to design this simulator, and its flow characteristics is analyzed through numerical simulation. The results indicate that the simulator is used not only to simulate the change of back-pressure caused by the change of engine operation condition, but also to distribute the mass flow into the two flowpaths linearly during the mode transition. The new simulator can keep the sum of the throttle ratios of turbojet/ramjet flowpaths as a constant in every moment during the process. For the inlet discussed in this paper, when the total throttle ratio is equal to 65% during the mode transition, the terminal shock locates in the throat of the TBCC inlet, the Mach number at the aerodynamic interface plane of this inlet is basically equal to 0.30, the flow ratio of this section is basically equal to 0.45, and the flow ratio into two flowpaths is distributed linearly. This simulator thus can meet the needs of expected goal.

Key words: airbreathing hypersonic propulsion system, turbine based combined cycle (TBCC), tandem type TBCC inlet, mode transition simulator, wind tunnel test

CLC Number:

V236

LIU Jun, YUAN Huacheng, GE Ning. Design and flow characteristics analysis of mode transition simulator for tandem type TBCC inlet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(12): 3675-3684.

References

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Design and flow characteristics analysis of mode transition simulator for tandem type TBCC inlet

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