turbine inlet temperature

With the development of aero-engine , the turbine inlet temperature is getting higher .

航空发动机的不断发展，使涡轮前的温度越来越高。

Modern advanced gas turbines usually use combined cooling methods to enhance cooling effect of blade in order to increase turbine inlet temperature .

现代先进燃气涡轮多采用复合冷却方式来对叶片进行强化冷却，以期提高涡轮前进口温度。

The fuel utilization and fuel flowrate to combustor were chosen to control the turbine inlet temperature .

选择燃料气利用率和燃烧室附加燃料流量作为燃气轮机透平初温的控制量。

With the increase of the turbine inlet temperature of high performance aero-engine day by day , the turbine coating blade coating technology has been widely used .

随着高性能航空发动机涡轮进口温度日益提高，涂层技术在涡轮叶片上得以广泛应用。

This paper introduces the parameter estimation research for the turbine inlet temperature and compressor exit pressure by using the engine variables measured under the different flight conditions .

本文研究利用不同飞行状态下测量的发动机变量估计涡轮进口温度和压气机出口压力。

Control of turbine inlet temperature and correction of turbine speed when thermodynamic performances of single shaft constant speed gas turbine generator set be tested on site

单轴恒速燃气轮发电机组现场热力性能试验中透平前温的控制及转速修正

For the turbine inlet temperature ( TIT ) of 850 ℃, the thermal efficiency of the new system may be expected to be as high as 48.10 % .

在透平初温为850℃的工况下，系统热效率高达48.11%。

The turbine inlet temperature of future gas turbines is expected to exceed 1700K . None of the traditional metal could work in this condition .

先进燃气涡轮的入口温度可超过1700K。

The use of highly efficient recuperator makes its single cycle efficiency as high as 30 % even though the turbine inlet temperature is only 875 ° C .

而高效回热器的使用，使得在透平进气温度在875°C的条件下，甚至能达到单循环效率30%左右。

The performance of aero engine ( thrust-to-weight ratio , specific fuel consumption ) can be improved by increasing the turbine inlet temperature and the compressor pressure ratio .

在提高压气机压比的同时，提升涡轮前温度是改善航空燃气涡轮发动机性能（推重比、耗油率）的有效措施。

With the increase of the turbine inlet temperature , the technique of high efficiency film cooling to decrease the blade surface temperature has become a hot topic of the turbine design .

随着涡轮进口温度的提高，采用高效气膜冷却降低叶片表面温度成为涡轮设计的主要目标之一。

With this technology to manufacture single crystal blades and vanes , turbine inlet temperature can be increased by 222 ￣ 333 ℃, and can reach as far as 2100 ￣ 2300K .

采用该技术制造单晶叶片，可使燃气涡轮入口温度提高222～333℃，达到2100～2300K。

Finally , we also analyse the influences of environment temperature , turbine inlet temperature , the efficiency of assemblies , drag in flow and regenerator effectiveness on the specific output and thermal efficiency of simple cycle and regenerative cycle .

最后还分析了环境温度、涡轮进口温度、各部件效率、流动阻力、回热度等因素对简单循环和回热循环的比功和循环效率的影响。

The results show that reheat cycle has much higher specific work than new cycle without reheat . Thermal efficiency of new cycle with reheat can be improved when total pressure ratio is big and low pressure turbine inlet temperature is high .

结果显示：与无再热新循环相比，再热使循环比功得到大幅提高；而再热循环热效率在低压透平入口温度较高，总压比较大时可得到较大幅度地提高。

Increasing turbine inlet gas temperature is one of important means to improve turbine efficiency and increase thrust-weight ratio .

提高涡轮前燃气温度是提高涡轮效率、增加推重比的重要手段之一。

With the increase of the turbine inlet gas temperature , the study on the thermal control of turbine vane endwall has become more and more important .

随着涡轮进口燃气温度水平不断提高，涡轮叶栅端壁区域的热控制成为研究的热点问题。

With the development of the aero-engine direction to the high thrust-weight ratio , and turbine inlet gas temperature continuously growing , the ability to endure temperature of existing high temperature alloys has been close to the limit .

随着航空发动机向高推重比方向发展，涡轮前燃气温度不断提高，现有高温合金材料的承温状况都己接近极限。

In order to improve efficiency of gas turbine , The turbine inlet temperature is increasing continuously .

先进燃气涡轮为了获得更高的效率，不断提高涡轮入口燃气温度。

Various methods to increase the surge margin and to decrease the power output are compared including compressor pressure ratio increase , compressor flow reduction , turbine critical area increase , turbine inlet temperature decrease and the compressor air extraction .

并对燃气轮机的各种调整通流能力的措施进行了分析比较，包括提高压气机压比、减小压气机流量、增加透平通流面积、降低透平进口温度以及空分整体化等。

Now improvement of gas turbine performance depends on cycle innovation and turbine inlet temperature elevation .

目前燃气轮机性能的改善依赖于循环的创新和透平进口温度的提高。