CN113047979A - 一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰 - Google Patents

一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰 Download PDF

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CN113047979A
CN113047979A CN202110357186.6A CN202110357186A CN113047979A CN 113047979 A CN113047979 A CN 113047979A CN 202110357186 A CN202110357186 A CN 202110357186A CN 113047979 A CN113047979 A CN 113047979A
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lobe
nozzle
small
lobed
crest
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盛志强
但誉
张澜
胡晓安
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Nanchang Hangkong University
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Nanchang Hangkong University
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78Other construction of jet pipes
    • F02K1/82Jet pipe walls, e.g. liners
    • F02K1/822Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • F02K1/825Infrared radiation suppressors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38Introducing air inside the jet
    • F02K1/386Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

本发明涉及一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰。以一个垂直于喷管轴线的横截面,切除带内斜切或扇形处理波瓣喷管外波瓣在横截面以后的部分,再从切除形成的新尾缘延伸出波瓣形扰流片,形成波瓣形波峰。波瓣形波峰由两侧小波峰,中间小波谷,及连接小波峰、小波谷的两小侧壁组成。本发明的优点和取得的有益效果为:采用波瓣形波峰的波瓣喷管,在引射进气和冲压进气情况下的掺混效率高。

Description

一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰
技术领域
本发明涉及一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰,采用波瓣形波峰的带内斜切或扇形处理波瓣喷管可用于军用直升机的红外抑制器,属于航空技术领域。
背景技术
军用直升机通过安装红外抑制器,来抑制动力装置产生的红外辐射,达到提升红外隐身性能,从而提高军用直升机的战场生存力。红外抑制器主体为波瓣喷管和弯曲混合管组成的波瓣混合器。直升机涡轴发动机的排气装置使用波瓣喷管,高速热排气流流经波瓣喷管,对周围环境大气形成引射作用。高速热排气流及被引射的环境气流流经波瓣喷管,因形成流向涡而在弯曲混合管内掺混,使最终排入大气的气流温度降低。除了利用引射作用引射环境气流,还可以利用直升机的向前飞行,使更多的环境气流冲压进混合管与热排气进行掺混,有利于进一步降低最终排入大气的气流温度。另外,热排气流在内被引射的环境气流在外,能够有效隔绝热排气流对周围壁面的直接加热。而为了控制红外抑制器的重量,减小加装红外抑制器对军用直升机飞行性能的影响,往往弯曲混合管的长度会受到限制,这时就需要提高波瓣喷管的掺混性能。
发明内容
本发明的目的在于提供一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰,在弯曲混合管的长度受限时,在引射或冲压环境大气进气时,采用波瓣形波峰替换原波峰,能获得更高的掺混效率。
本发明通过如下技术方案实现。
一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰,以一个垂直于喷管轴线的横截面,切除带内斜切或扇形处理波瓣喷管外波瓣在横截面以后的部分,再从切除处形成的新尾缘延伸出波瓣形扰流片,形成波瓣形波峰,波瓣形波峰轴向尺寸为切除部分轴向尺寸的1.5~2.5倍。
进一步,所述的波瓣形波峰由两侧小波峰,中间小波谷,及连接小波峰和小波谷的两小侧壁组成,两小侧壁夹角为40°~60°。
与现有技术相比,本发明的优点和取得的有益效果为:
第一,引射进气时掺混效率高。切除带内斜切或扇形处理波瓣喷管部分外波瓣后,再从外波瓣延伸出波瓣形扰流片形成波瓣形波峰,在环境气流为引射进气时,能够促进波峰尾流区的掺混,对其他区域的掺混影响小,从而获得更高的掺混效率;
第二,冲压进气时掺混效率高。波瓣形波峰相对原波峰,径向位置更靠外,在环境气流为冲压进气时,外波瓣通道热排气能够保持在径向靠外侧,利于波峰尾流区冲压进气的环境气流与热排气流的掺混,对其他区域的掺混影响小,从而获得更高的掺混效率。
附图说明
图1为本发明中剑形深波谷交变波瓣喷管的等轴视图。
图2为本发明中波瓣形波峰剑形深波谷交变波瓣喷管的等轴视图。
图3为本发明中波瓣形波峰剑形深波谷交变波瓣喷管的局部等轴视图。
图4为本发明中波瓣形波峰剑形深波谷交变波瓣喷管的后视图。
图5为本发明中波瓣形波峰剑形深波谷交变波瓣喷管的前视图。
图6为本发明中波瓣形波峰剑形深波谷交变波瓣喷管的侧视图。
在附图中,1为波瓣形波峰;2为外波瓣;3为小波峰;4为小波谷;5为小侧壁。
具体实施方式
下面将结合附图1~6和实施例对本发明进行进一步详细说明。
一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰,以一个垂直于喷管轴线的横截面,切除带内斜切或扇形处理波瓣喷管(构型中带内斜切处理)外波瓣2在横截面以后的部分,再从切除处形成的新尾缘延伸出波瓣形扰流片,形成波瓣形波峰1,波瓣形波峰轴向尺寸为切除部分轴向尺寸的1.5~2.5倍。本实施例具体为2倍。
作为本发明实施例的进一步改进,所述的波瓣形波峰1由两侧小波峰3,中间小波谷4,及连接小波峰3和小波谷4的两小侧壁5组成,两小侧壁夹角为40°~60°。本实施例具体的两小侧壁夹角为50°。
以上所述实施方式仅为本发明的优选实施例,而并非本发明可行实施的穷举。对于本领域的一般技术人员而言,在不背离本发明原理和精神的前提下对其所做出的任何显而易见的改动,都应当被认为包含在本发明的权利要求保护范围之内。因此,本发明的保护范围应以所述权利要求的保护范围为准。

Claims (2)

1.一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰,其特征在于,以一个垂直于喷管轴线的横截面,切除带内斜切或扇形处理波瓣喷管外波瓣(2)在横截面以后的部分,再从切除处形成的新尾缘延伸出波瓣形扰流片,形成波瓣形波峰(1),波瓣形波峰轴向尺寸为切除部分轴向尺寸的1.5~2.5倍。
2.根据权利要求1所述的用于带内斜切或扇形处理波瓣喷管的波瓣形波峰,其特征在于,所述的波瓣形波峰(1)由两侧小波峰(3),中间小波谷(4),及连接小波峰(3)和小波谷(4)的两小侧壁(5)组成,两小侧壁夹角为40°~60°。
CN202110357186.6A 2021-04-01 2021-04-01 一种用于带内斜切或扇形处理波瓣喷管的波瓣形波峰 Pending CN113047979A (zh)

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CN116104661B (zh) * 2023-03-17 2023-08-25 南京航空航天大学 一种可调深浅波瓣喷管结构及调节方法

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Application publication date: 20210629