大直径小环腔燃烧室设计及试验

邬俊; 陈敏敏; 陈翔; 张险; 康尧; 汤姣; 刘达兵; 郭青林; 杨志

doi:10.13224/j.cnki.jasp.20220115

大直径小环腔燃烧室设计及试验

doi: 10.13224/j.cnki.jasp.20220115

中国航发湖南动力机械研究所，湖南株洲 412002

详细信息

作者简介:
邬俊（1986-），男，高级工程师，硕士，主要从事航空发动机燃烧室设计方面的研究

中图分类号: V231.3
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- 文章访问数: 120
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- 被引次数: 0
出版历程
- 收稿日期: 2022-03-06
- 网络出版日期: 2023-02-07

Design and experiment of grand scale diameter and small annular cavity combustor

Hunan Aviation Powerplant Research Institute， Aero Engine Corporation of China，Zhuzhou Hunan 412002，China

摘要

摘要:
针对某创新构型的涡轮发动机，在国内首次开展大直径小环腔燃烧室的设计及试验研究。提出基于扩压器逆向进气条件下的环涡流场匹配切向燃油喷射的燃烧室设计方案，开展不同状态下燃烧室冷态及热态性能试验，得到燃烧室流阻特性、地面点火特性、贫油熄火特性以及燃烧效率、出口温度场等特性，结果表明：①该设计方案可以满足燃烧室的设计要求；②与常规燃烧室相比，该方案的喷嘴间距比设计达到1.65；③该方案燃烧室的点火性能优异，最低贫油点火油气比达到0.016，点火联焰时间可在4 s以内；④该方案燃烧室的总压损失、燃烧效率、出口温度分布系数（OTDF）、出口径向温度分布系数（RTDF）等综合性能优异，其中慢车状态的燃烧效率能够达到98.6%，设计点的OTDF达到0.16。
- 涡轮发动机 /
- 大直径 /
- 小环腔 /
- 燃烧室设计 /
- 性能试验
Abstract:
Design and experiment study of a grand scale diameter and small annular cavity combustor were carried out for the first time interiorly, considering the turbine engine with innovated structure. A combustor design scheme based on annular vortex field matching tangential fuel injection under the condition of diffuser with reverse air intake was proposed. Cold and hot performance experiments of combustor under different conditions were carried out, the combustor characteristics including flow resistance characteristics, ignition characteristics at ambient temperature and pressure, lean blow out characteristics, combustion efficiency, as well as the outlet temperature field, were obtained. The results showed that: （1） the design scheme met the design requirements of combustor; （2） compared with conventional combustor, the nozzle spacing ratio of the scheme reached 1.65; （3） the ignition performance of the designed combustor was excellent, as its minimum lean ignition fuel-air-ratio reached 0.016 and its ignition and flame combination time was within 4 s; （4） the total pressure loss, combustion efficiency, out temperature distribution factor （OTDF） and radial temperature distribution factor （RTDF） of the designed combustor had outstanding performance; as the combustion efficiency of idle state reached 98.6%, the OTDF of design point reached 0.16 as well.
- turbine engine /
- grand scale diameter /
- small annular cavity /
- combustor design /
- performance experiments

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图 1 大直径、小环腔燃烧室总体结构布局及气动流路

Figure 1. Overall structure and flow path of the grand scale diameter and small annular cavity combustor

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图 2 燃烧室纵截面速度分布和流线图

Figure 2. Distribution of velocity and streamlines on longitudinal section of combustor

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图 3 燃油轨迹

Figure 3. Fuel trajectory

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图 4 常温常压点火试验装置

Figure 4. Schematic of test facility at ambient temperature and pressure

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图 5 出口截面测点分布示意图

Figure 5. Distribution of measurement points on the exit section

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图 6 常温常压点火性能

Figure 6. Ignition boundary at ambient temperature and pressure

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图 7 某状态点火试验监控曲线

Figure 7. Monitoring curves of ignition experiment in a certain state

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表 1 燃烧室主要设计参数

Table 1. Main design parameters of combustor

参数	数值
空气流量/（kg/s）	3.2
进口总压/MPa	0.66
进口总温/℃	272
出口总温/℃	947
扩压器出口外径/mm	600
涡轮进口外径/mm	700
总压损失/%	≤5
燃烧效率	≥0.95
出口温度分布系数	≤0.3

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表 2 点火状态参数

Table 2. Parameters of ignition experiment

状态	进气流量/ （kg/s）	高度/m	进气温度	进气压力
1	0.20	0	常温	常压
2	0.25
3	0.30
4	0.35
5	0.40

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表 3 性能试验状态参数

Table 3. Parameters of performance experiment

状态	进气压力/ MPa	进气温度/℃	进气流量/ （kg/s）	燃油流量/ （g/s）
A	0.661	274	3.21	62.3
B	0.243	113	1.38	16.6

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表 4 燃烧室性能试验结果

Table 4. Parameters of performance experiment of combustor

状态	总压损失/%	t₄/℃	OTDF	RTDF	燃烧效率/%
A	3.7	958.0	0.16	0.008	99.9
B	3.3	624.3	0.25	0.007	98.6

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