带连续爆震加力燃烧室的涡轮发动机循环及推进性能研究

Thermal Cycle and Propulsive Performance of Turbine Engine with Continuous Detonation Afterburner

关键词:  涡轮发动机  加力燃烧室  连续爆震  推进性能  性能模型

Key words:  Turbine engine  Afterburner  Continuous detonation  Propulsive performance  Performance model

摘要:

为进一步提升现有涡轮喷气发动机推进性能，可以采用连续爆震加力燃烧室，针对此，本文首先建立考虑了三种耦合热力过程的连续爆震燃烧室热力过程分析模型，通过与传统涡轮发动机性能分析模型相耦合，分析了带连续爆震加力燃烧的涡轮发动机推进性能及加力燃烧室部件特性。结果表明，由于连续爆震燃烧室具有自增压特性，将其替代传统加力燃烧室可以显著提升加力时涡轮发动机性能；但另一方面，作为加力燃烧室，由于涡轮后气流温度过高，导致连续爆震加力燃烧室增压比的降低，通过对发动机循环参数的选择可以得到改善；同时，连续爆震加力燃烧室部件特性还受到燃烧室进气损失、反应物填充速度及反应物提前燃烧比例的影响。

Abstract:

In order to improve the propulsive performance of conventional turbine engine， a continuous detonation afterburner can be used. An analytical model of thermodynamic process for the continuous detonation afterburner is established， which considers three kinds of coupled thermodynamic processes. By coupling the model with performance analytical model of conventional turbine engine， the propulsive performance and component characteristics of turbine engine with continuous detonation afterburner are investigated. The results show that the performance of turbine engine can be significantly enhanced by replacing the conventional afterburner with the continuous detonation afterburner because of its pressure-gain characteristics. On the other hand， the high temperature of the gas flow behind the turbine has negative effect on the pressure-gain of continuous detonation afterburner. This adverse effect can be weakened by carefully selecting cycle parameters of the engine. The component characteristics of continuous detonation afterburner are also affected by the inlet loss of combustor， the filling velocity of reactants and the mass fraction of deflagration products.