共查询到20条相似文献,搜索用时 93 毫秒
1.
2.
对6FA燃气轮机试车台的燃油控制阀进行性能研究,阐述了试车台燃气轮机燃油组成、燃油控制阀的性能和故障反馈等。通过阀门的性能特性曲线和执行机构的性能分析,重点讨论了6FA燃气轮机试车台的燃油控制阀位置控制和反馈性能,并对燃油控制阀在运行过程中会出现的故障以及反馈动作进行探讨。试车台的燃料选用与目前燃气轮机电站所用的天然气燃料不同,对6FA燃气轮机试车台燃油控制阀的性能分析,可为同类型燃气轮机试车台的燃油系统搭建提供借鉴和参考。 相似文献
3.
开展离心式燃油喷嘴雾化仿真研究,为燃气轮机燃烧提供依据。利用Solidworks、ANSYS ICEM CFD软件进行离心式喷嘴外场建模和网格划分,基于FLUENT仿真完成不同压力工况下瞬态离心式喷嘴外流场数值模拟计算。对离心式喷嘴在无辅助空气作用下和有空气辅助作用下的外流场进行了数值模拟研究,分析其在13个压力点工况下(0.05 MPa、0.1 MPa、0.3 MPa、0.5 MPa、1.0 MPa、1.5 MPa、2.0 MPa、2.5 MPa、3.0 MPa、4.0 MPa、5.0 MPa、6.0 MPa、7.0 MPa)的雾化液滴分布以及性能参数的结果。研究表明:在无空气辅助下,喷嘴的雾化液滴分布都呈圆锥状分布,喷嘴在压力点工况下的整体索太尔平均直径(SMD)以及不均匀度的极大值(极小值)分别为 414.54 μm(40 μm)、0.670 9(0.487 4);在3个不同空气压力下(10 kPa、14 kPa、20 kPa),喷嘴的雾化液滴分布都呈圆锥状分布,喷嘴在压力点工况下的整体SMD以及不均匀度的极大值(极小值)分别为35.93 μm(15.67 μm)、0.838 7(0.704 0)。本文的仿真研究为离心式燃油喷嘴应用到燃气轮机燃烧中提供了依据 相似文献
4.
5.
6.
7.
8.
9.
10.
11.
Hongzhao Liu Huifeng Gao Shilie Weng 《Energy Sources, Part A: Recovery, Utilization, and Environmental Effects》2018,40(18):2154-2162
With the micro gas turbine is used more and more widely, the operating conditions become complex and fluctuating which impacts the environmental friendliness of combustor. In this work, a low swirl premixed nozzle (LSPN) is designed based on the original premixed nozzle (OPN) of a 60 kW micro gas turbine, in order to adapt the flexibility of load and operating environment by improving the mixing performance of fuel and air. The flow and combustion characteristics of LSPN and OPN fed by natural gas is numerically studied using the standard k-ε model and the combined Finite Rate Chemistry/Eddy Dissipation Model (FRC/EDM) under various operating conditions. The results show that the mixing performance of air and fuel in LSPN has been improved. The flow unmixedness in LSPN is always smaller than OPN, and it is 41.74% lower at the outlet of the nozzle. While the equivalence ratio decreases, the mean temperature in the combustor decline. Furthermore, under the majority of operating conditions, the emission performance of LSPN is better than OPN. 相似文献
12.
在喷油泵综合实验台上采用先进的EFS瞬时喷油量测量仪,对8套不同结构参数的共轨喷油器喷嘴进行了喷油规律的测试,研究了喷孔数、喷孔直径、喷孔长度以及喷孔夹角等参数对喷油规律的影响。 相似文献
13.
《Combustion and Flame》2006,144(1-2):225-236
The thermochemical states of three swirling CH4/air diffusion flames, stabilized in a gas turbine model combustor, were investigated using laser Raman scattering. The flames were operated at different thermal powers and air/fuel ratios and exhibited different flame behavior with respect to flame instabilities. They had previously been characterized with respect to their flame structures, velocity fields, and mean values of temperature, major species concentrations, and mixture fraction. The single-pulse multispecies measurements presented in this article revealed very rapid mixing of fuel and air, accompanied by strong effects of turbulence–chemistry interactions in the form of local flame extinction and ignition delay. Flame stabilization is accomplished mainly by hot and relatively fuel-rich combustion products, which are transported back to the flame root within an inner recirculation zone. The flames are not attached to the fuel nozzle, and are stabilized approximately 10 mm above the fuel nozzle, where fuel and air are partially premixed before ignition. The mixing and reaction progress in this area are discussed in detail. The flames are short (<50 mm), especially that exhibiting thermoacoustic oscillations, and reach a thermochemical state close to adiabatic equilibrium at the flame tip. The main goals of this article are to outline results that yield deeper insight into the combustion of gas turbine flames and to establish an experimental database for the validation of numerical models. 相似文献
14.
在涡轮增压器热试台架上进行涡轮和压气机效率特性测量时,由于高温涡轮与相对温度较低的压气机之间有明显温差,造成热量从涡轮传向压气机,会使测量得到的涡轮和压气机的效率分别高于和低于实际值。本文对增压器的热传递现象进行了分析,并通过一种有效计算方法对涡轮和压气机的效率特性进行了热传递校准。校准后的涡轮和压气机效率特性与增压器冷试台架上测得的数据符合较好,最大误差低于4.7%。 相似文献
15.
通过分析国外机组资料和实际燃料切换运行曲线,逆推双燃料切换控制策略,并利用现有燃烧试验台,在保证燃烧室出口温度稳定波动的前提下,对规定时间内完成燃料快速切换的燃烧室内火焰稳定性加以验证。试验结果表明:某型机组试验可依据理论切换时间30 s换算燃机最大负荷时燃料的变化量,保证机组在60 s内完成燃料的快速切换,在此切换过程中,燃烧室内火焰稳定,动态压力最大值为4.55 k Pa。由于燃烧试验台条件与整机试验环境存在较大的差异性,试验过程得出燃料变化量仅可作为参考,主要用于减少整机试验次数并规避试验风险,最终值仍应以整机试验结果为准。 相似文献
16.
An overview on dry low NOx micromix combustor development for hydrogen-rich gas turbine applications
《International Journal of Hydrogen Energy》2019,44(13):6978-6990
The paper presents a survey of the interactive optimization cycle at Aachen University of Applied Sciences, used for the development of a new low emission Micromix combustor module for application in hydrogen fueled industrial gas turbines. During the development process, experimental and numerical methods are applied to optimize a given baseline combustor with 0.3 mm nozzles with respect to combustion efficiency, combustion stability, higher thermal power output per nozzle and reduced manufacturing complexity.Within the described research cycle combustion and flow simulations are used in the context of parametric studies for generating optimized burner geometries and the phenomenological interpretation of the experimental results. Experimental tests, carried out on an atmospheric combustion chamber test stand provide the basis for validation of simulation results and proof of the predicted combustion characteristics under scaled down gas turbine conditions.In the presented studies, an integration-optimized Micromix combustor with a nozzle diameter of 0.84 mm is tested at atmospheric pressure over a range of gas turbine operating conditions with hydrogen fuel. The combustor module offers an increase in the thermal power output per nozzle by approx. 390% at a significant reduced number of injectors when compared to the baseline design. This greatly benefits manufacturing complexity and the robustness of the combustion process against fuel contamination by particles.During atmospheric testing, the optimized combustor module shows satisfactory operating behavior, combustion efficiency and pollutant emission level. Within the evaluated operating range, which correlates to gas turbine part-, full- and overload conditions, the investigated combustor module exceeds 99% combustion efficiency. The Micromix combustor achieves NOx emissions less than 2.5 ppm corrected to 15 Vol% O2 at the design point.Based on numerical analyses and experimental low pressure testing, a full-scale gas turbine combustion chamber is derived. High pressure testing in the auxiliary power unit Honeywell/Garrett GTCP 36–300 shows stable operation during acceleration of the engine, during IDLE and during load variations between IDLE and Main Engine Start (MES) mode. Throughout the investigated operating range, the combustion chamber generates low NOx emissions under full-scale gas turbine conditions. 相似文献
17.
18.
为提升船用低速机涡轮增压器性能,对增压器涡轮排气壳底部流道结构进行参数化,设计并开展了以效率为优化目标的四因素三水平正交试验优化设计和增压器整机性能试验。首先,采用CFD数值模拟方法对不同参数组合的涡轮气动性能进行了计算,然后对涡轮排气壳底部流道结构参数开展了灵敏度分析,同时针对不同参数组结构开展了内部流场对比分析,明确结构因素对流动的影响机理;在此基础上对优化后方案开展了涡轮特性分析,最后在低速双燃料机平台上开展增压器整机试验验证。分析研究表明:在涡轮进气壳、喷嘴环和涡轮叶片等通流部件结构不变的前提下,涡轮排气壳排气方向轴向长度对涡轮整级效率的影响最大,优化后效率明显提升,设计点总压损失系数降低0.3874,静压恢复系数提升0.537,总静效率提升1.85%,其余工况总静效率最大提升2.4%。试验结果表明:优化后涡轮增压器整机效率在主机燃油模式和燃气模式下的全工况范围内效率均有提升,最大提升幅度分别达到1.4%和2.1%,涡轮性能和增压器整机性能改善明显。 相似文献
19.
为适应生物质气低热值、组分变化大的特点,达到燃烧室燃烧稳定、低排放要求,在某60 kW级微型燃气轮机环形燃烧室结构的基础上,新设计了一种具有不同预混孔结构的新喷嘴,并在上海交通大学微型燃气轮机单喷嘴燃烧室实验台上对原喷嘴及新设计喷嘴进行冷态流动实验,对比分析不同稀释孔直径及工质参数条件下原喷嘴及新喷嘴对燃烧室空气流量分配比及过量空气系数的影响。研究表明:燃料流量、空气流量变化会影响燃烧室空气流量分配,空气温度变化对燃烧室空气流量分配无影响;燃料热值降低会导致燃烧室过量空气系数增大,需要匹配直径更大的燃烧室稀释孔;相比于原喷嘴新喷嘴的流量分配比较大,为使其适应低热值燃料,需要匹配的燃烧室稀释孔直径为11.0 mm,该条件下新喷嘴可适应CH_4摩尔分数为50%~90%的燃料。 相似文献
20.
振荡燃烧是贫燃预混燃烧室普遍面临的不稳定燃烧现象,该现象会导致发动机振动,污染物排放加剧,喷嘴烧蚀等,因此需要对这种现象进行控制,以减小压力脉动。本文针对某型低排放燃烧室,以对值班燃料供给控制为核心,设计了一套振荡燃烧主动控制系统,并进行了试验研究。分析了燃烧室内压力脉动控制的影响因素和变化规律,试验研究表明:(1)该系统有效地抑制了燃烧室的压力脉动。(2)控制系统投入工作的相位不同时,抑制效果明显变化。(3)该系统对由贫燃燃烧不稳定引起的压力脉动有明显抑制效果,对其他原因引起的脉动无明显抑制效果。 相似文献