涡轮导向器喉道尺寸对燃气涡轮起动机性能的影响

樊小倩; 汪洋冰; 刘一鸣; 白杰

doi:10.13224/j.cnki.jasp.20230775

涡轮导向器喉道尺寸对燃气涡轮起动机性能的影响

doi: 10.13224/j.cnki.jasp.20230775

樊小倩^{1, 2,},
汪洋冰^{1, 2},
刘一鸣¹,
白杰¹

1.
中国航空工业集团有限公司金城南京机电液压工程研究中心，南京 211106
2.
中国航空工业集团有限公司航空机电系统综合航空科技重点实验室，南京 211106

基金项目: 集团创新专项（YY20012-02）

详细信息

作者简介:
樊小倩（1989-），女，工程师，硕士，研究领域为燃气涡轮起动机设计及涡轮气动热力学。E-mail：wsfxqsydx@163.com

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2023-12-09
- 网络出版日期: 2024-04-19

Effect of throat size of turbine guide on performance of gas turbine starter

FAN Xiaoqian^{1, 2
,},
WANG Yangbing^{1, 2},
LIU Yiming¹,
BAI Jie¹

1.
Jincheng Nanjing Engineering Institute of Aircraft Systems，Aviation Industry Corporation of China，Limited，Nanjing 211106，China
2.
Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration，Aviation Industry Corporation of China，Limited，Nanjing 211106，China

摘要

摘要:
本文以某燃气涡轮起动机的燃气涡轮导向器为研究对象，采用试验及数值模拟方法研究了燃气涡轮导向器喉道尺寸对燃气涡轮起动机整机及部件性能的影响。针对A、B、C型三种燃气涡轮导向器（喉道平均外径分别为ϕ111.27 mm、ϕ111.94 mm、ϕ112.34 mm）的试验研究结果表明：C型燃气涡轮起动机较A型燃气涡轮起动机，正常起动时间缩短14%，失效起动输出轴脱开转速升高7.1%，最大输出功率增加11.6%，起动机性能显著提高。数值结果表明：C型较A型涡轮级流量增加3.6%，动力涡轮最大输出功率增加12.2%，动力涡轮功率增加归因于流量增加、温度增加、温降增加的叠加效应。总之，燃气涡轮导向器喉道外径通过影响涡轮级性能改变了燃气涡轮起动机整机的匹配特性，使整机性能存在一定的分散性。
- 燃气涡轮起动机 /
- 涡轮导向器 /
- 喉道尺寸 /
- 外径 /
- 动力涡轮 /
- 输出功率
Abstract:
This article takes a gas turbine guide used on a gas turbine starter as the research object, and the effect of throat size of gas turbine guide on the performance of gas turbine starter and components were studied using experimental methods and numerical simulation. The results of experimental reseach on A、B、C three types of gas turbine guide (average outer diameter of the throat is ϕ111.27 mm、ϕ111.94 mm、ϕ112.34 mm) indicates: type C starter compared to type A starter, normal starting time becomes shorter by 14%, output shaft disengagement speed of lose efficacy starting increases by 7.1%, maximum output power increases by 11.6%, the performance of starter is improved significantly. Numerical research results indicates: type C compared to type A, the flow rate of turbine stage increases by 3.6%, maximum output power of power turbine increases by 12.2%. The increase in power turbine power is attributed to the combined effect of increased flow rate、increased temperature and increased temperature drop. In summary, the outer diameter of gas turbine guide throat changes the matching point of entire gas turbine by affecting the performance of turbine stage, then the overall performance exists a certain degree of dispersion.
- gas turbine starter /
- turbine guide /
- throat size /
- outer diameter /
- power turbine /
- output power

HTML

图 1 燃气涡轮起动机结构

Figure 1. Structural diagram of gas turbine starter

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图 2 起动机核心机

Figure 2. Core engine of starter

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图 3 燃气涡轮导向器结构示意图

Figure 3. Schematic diagram of gas turbine guide

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图 4 燃气涡轮起动机试验台示意图

Figure 4. Schematic diagram of gas turbine starter experimental bench

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图 5 飞轮结构

Figure 5. Flywheel struture

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图 6 第一次正常起动输出性能

Figure 6. Output performance of the first normal start

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图 7 数值模拟几何模型

Figure 7. Numerical simulation geometry model

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图 8 网格S1图

Figure 8. grid S1 diagram

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图 9 动力涡轮输出性能

Figure 9. Output performance of power turbine

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图 10 沿流向各界面参数变化趋势

Figure 10. Trend of parameter changes at various interfaces along the flow direction

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表 1 外径尺寸计量结果

Table 1. Outer diameter measurement results

导向器代号	计量尺寸/mm	设计尺寸/mm
A	ϕ111.18～ϕ111.36	$ {\phi }1{11.6}_{-0.35}^{+0.67} $ （$ {\phi } $111.25～$ {\phi } $112.27）
B	ϕ111.89～ϕ111.99
C	ϕ112.22～ϕ112.46

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表 2 第一次正常起动试验条件

Table 2. Conditions for the first normal start experiment

导向器	大气压力/hPa	大气温度/K	燃气涡轮转速/（r/min）
A	1016	302.1	63605
B	1018	304.6	63415
C	1016	302	63371

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表 3 整机性能数据及修正值

Table 3. Overall performance data and corrected value

起动机	序号	起动类型	大气压力/hPa	大气温度/K	起动工作时间/s		燃气涡轮转速/（r/min）		压气机出口压力/ hPa		输出轴脱开转速/（r/min）		最大输出功率/kW
起动机	序号	起动类型	大气压力/hPa	大气温度/K	实测	修正	实测	修正	实测	修正	实测	修正	实测	修正
A型	1	正常起动	1016	302.1	33	30.6	63605	63680	1990	2120	5680		39.8
	2	失效起动	1016	302.7	58.8		63649	63727	1980	2110	3038	3243	40.4	44.7
	3	失效起动	1015	302.6	58.8		63678	63755	2010	2140	3062	3268	40.9	45.3
	4	正常起动	1017	303.1	33.6	31	63605	63685	1970	2110	5755		41.8
B型	1	正常起动	1018	304.6	30.1	27.3	63415	63503	1920	2070	5655		44.1
	2	失效起动	1016	305.2	58.9		63488	63579	1900	2050	3176	3417	43.3	48.6
	3	失效起动	1020	304.5	59		63517	63604	1920	2070	3213	3433	44.1	49
	4	正常起动	1013	307.9	30.9	27.5	63444	63549	1880	2060	5673		43.7
C型	1	正常起动	1016	302	28.7	26.3	63371	63445	1920	2050	5660		45.8
	2	失效起动	1014	303.1	58.6		63547	63627	1910	2050	3257	3473	45	49.9
	3	失效起动	1015	304.2	58.8		63517	63603	1900	2050	3245	3474	44.8	50
	4	正常起动	1016	303.6	28.2	25.5	63415	63498	1890	2040	5673		46.6

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表 4 试验结果对比

Table 4. Comparion of experimental results

试验参数	A型起动机	B型起动机	C型起动机	变化量/%
正常起动工作时间/s	30.6	27.3	26.3	-14
失效起动脱开转速/（r/min）	3243	3417	3473	7.1
最大输出功率/kW	44.7	48.6	49.9	11.6
离心压气机压比	3.09	3.04	3.02	-2.3

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表 5 数值计算条件

Table 5. Numerical calculation conditions

参数	数值
环境温度/K	288
环境压力/hPa	1013
离心压气机压比	3.2
燃烧室总压恢复系数	0.95
燃烧室出口温度/K	1100
燃气涡轮转速/（r/min）	64000

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表 6 最大功率点性能对比

Table 6. Comparison of maximum power point performance

计算参数	A模型	B模型	C模型	变化量/%
导向器喉道外径/mm	$\phi $111.27	$\phi $111.94	$\phi $112.34
流量$ {W}_{\mathrm{t}\mathrm{h}} $/（kg/s）	0.6425	0.6565	0.6657	3.6
燃气涡轮出口温度$T_1^* $/K	960.4	964.5	967.3	0.73
燃气涡轮出口压力$p_1^* $/hPa	1626.2	1661	1684.7	3.6
燃气涡轮级膨胀比p^/$p_1^ $	1.894	1.854	1.828	−3.5
燃气涡轮级温降$ \nabla {T}_{1} $/K	139.6	135.5	132.7	−4.9
燃气涡轮输出功率/kW	102.9	102.2	101.4	−1.5
动力涡轮出口温度$T_2^* $/K	887.8	888.2	888.6	0.1
动力涡轮出口压力$p_2^* $/hPa	1095.1	1097.7	1100	0.45
动力涡轮级膨胀比$p_1^* $/$p_2^* $	1.485	1.513	1.532	3.2
动力涡轮级温降$ \nabla {T}_{2} $/K	72.6	76.3	78.7	8.4
动力涡轮输出功率/kW	52.6	56.4	59	12.2
出口总温$T_0^* $/K	887.8	888.2	888.7	0.1
出口总压$p_0^* $/hPa	1083.5	1085.5	1087.5	0.37

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