利用热重分析仪(TG)、气相色谱-质谱联用仪(GC/MS)与固定床反应器,考察了微藻、核桃壳及混合物主要热解阶段的需热量特性,以及混合比、温度、催化剂种类对二者混合热解制备芳烃的影响规律。结果表明:在不同升温速率下,核桃壳热解在180~...利用热重分析仪(TG)、气相色谱-质谱联用仪(GC/MS)与固定床反应器,考察了微藻、核桃壳及混合物主要热解阶段的需热量特性,以及混合比、温度、催化剂种类对二者混合热解制备芳烃的影响规律。结果表明:在不同升温速率下,核桃壳热解在180~270℃和380~485℃处存在两个吸热峰,整体表现为吸热效应(378.56~596.45k J·kg^(-1));微藻热解在280~450℃处存在一个放热峰,整体表现为放热效应(-814.76~^(-1)191.52 k J·kg^(-1))。微藻/核桃壳热解呈现较低的放热效应(-99.05~^(-1)58.04 k J·kg^(-1)),表明二者混合热解可以实现一定程度的热量耦合。微藻/核桃壳热解在制备芳烃上表现出明显的协同效应,且芳烃相对含量在600℃、混合比1:1下达到最大值,为20.51%;加入Cu/HZSM-5可进一步提高混合热解的芳烃相对含量,达到35.74%。为微藻与核桃壳的高值化利用提供了新思路。展开更多
Tip leakage flow affects the flow stability of high-loading compressors significantly.Therefore,a novel approach via induced shock wave near suction-side edge of blade tip was proposed to suppress the strength and inf...Tip leakage flow affects the flow stability of high-loading compressors significantly.Therefore,a novel approach via induced shock wave near suction-side edge of blade tip was proposed to suppress the strength and influence range of leakage flow in a transonic rotor.Three new schemes with different circumferentially diverging degrees of clearance were designed to reveal the mechanism of the new approach.Through the action of the circumferentially diverging clearance(from the pressure side to the suction side over blade tip),a much more dramatic acceleration of the supersonic leakage jet flow appeared over blade tip of the new schemes.An induced shock wave was produced near the suction side edge of blade tip due to the pressure difference between the discharging leakage flow and the surrounding high-pressure mainflow in tip channel.As a result,both the mass flow rate and the outlet velocity of leakage flow were reduced significantly via the induced shock wave.Meanwhile,the suppressing effect of the new approach on the tip leakage jet flow was closely related to the strength and circumferential location of the induced shock wave.With the aids of the induced shock wave,the largest improvement of tip flow characteristics with an over 5%increase in stall margin was realized in new transonic rotor when the circumferential divergence angle equals 8°,accompanied with no more than a 0.4%decrease in isentropic efficiency.展开更多
文摘利用热重分析仪(TG)、气相色谱-质谱联用仪(GC/MS)与固定床反应器,考察了微藻、核桃壳及混合物主要热解阶段的需热量特性,以及混合比、温度、催化剂种类对二者混合热解制备芳烃的影响规律。结果表明:在不同升温速率下,核桃壳热解在180~270℃和380~485℃处存在两个吸热峰,整体表现为吸热效应(378.56~596.45k J·kg^(-1));微藻热解在280~450℃处存在一个放热峰,整体表现为放热效应(-814.76~^(-1)191.52 k J·kg^(-1))。微藻/核桃壳热解呈现较低的放热效应(-99.05~^(-1)58.04 k J·kg^(-1)),表明二者混合热解可以实现一定程度的热量耦合。微藻/核桃壳热解在制备芳烃上表现出明显的协同效应,且芳烃相对含量在600℃、混合比1:1下达到最大值,为20.51%;加入Cu/HZSM-5可进一步提高混合热解的芳烃相对含量,达到35.74%。为微藻与核桃壳的高值化利用提供了新思路。
基金sponsored by the General Program of National Natural Science Foundation of China (Grant No.52076124)the National Science and Technology Major Project (Grant No.J2019-Ⅱ-0014-0035)
文摘Tip leakage flow affects the flow stability of high-loading compressors significantly.Therefore,a novel approach via induced shock wave near suction-side edge of blade tip was proposed to suppress the strength and influence range of leakage flow in a transonic rotor.Three new schemes with different circumferentially diverging degrees of clearance were designed to reveal the mechanism of the new approach.Through the action of the circumferentially diverging clearance(from the pressure side to the suction side over blade tip),a much more dramatic acceleration of the supersonic leakage jet flow appeared over blade tip of the new schemes.An induced shock wave was produced near the suction side edge of blade tip due to the pressure difference between the discharging leakage flow and the surrounding high-pressure mainflow in tip channel.As a result,both the mass flow rate and the outlet velocity of leakage flow were reduced significantly via the induced shock wave.Meanwhile,the suppressing effect of the new approach on the tip leakage jet flow was closely related to the strength and circumferential location of the induced shock wave.With the aids of the induced shock wave,the largest improvement of tip flow characteristics with an over 5%increase in stall margin was realized in new transonic rotor when the circumferential divergence angle equals 8°,accompanied with no more than a 0.4%decrease in isentropic efficiency.