高压涡轮主动间隙控制引气风斗流动特性实验

高压涡轮主动间隙控制(high-pressure turbine with active clearance control,HPTACC)引气风斗流动特性将对发动机的效率和安全运转产生较大影响,为此开展HPTACC引气风斗流动特性实验。在出口背压一定状态下,通过改变马赫数和节流孔板直径,获得引气风斗的总压恢复系数等特性规律。实验结果表明:在来流马赫数较低的工况下,引气风斗的总压恢复系数约0.99,流动损失较小。随着马赫数和引气风斗流量的增大总压恢复系数下降,KD3在0.46马赫数时相较于0.19马赫数总压恢复系数下降了11%,0.46马赫数时KD3相较于KD1的总压恢复系数下降了6.5%。引气风斗在马赫数较小时出口总压沿径向分布较均匀;马赫数增加后不均匀度加大。

Flow characteristic experiment on air bleeding manifold of high-pressure turbine

The flow characteristics of the air bleeding manifold of high-pressure turbine with active clearance control (HPTACC) have great impact on engine efficiency and safe operation. Therefore, flow characteristics experiments of the air bleeding manifold of HPTACC were performed to obtain the total pressure recovery coefficient and other flow characteristics under certain outlet back pressure with changeable parameters of Mach number and the diameter of throttle orifice plate. Results indicate that the flow losses are small un-der low Mach number with the total pressure recovery coefficient of around 0.99. With the increase of Mach number and the flow of air bleeding, the total pressure recovery decreased. When the opening degree was KD3, the total pressure recovery coefficient under Mach number of 0.46 was decreased by 11% compared to that with Mach number of 0.19; when Mach number was 0.46, the total pressure recovery co-efficient under KD3 was decreased by 6.5% compared to that of KD1. The radial distributions of outlet total pressure were uniform under low Mach number and tended to be less uniform with the increase of Mach number.