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本发明涉及一种喷孔交替布置的支板火焰稳定器，支板火焰稳定器主要由V型面、垂直尾缘和燃料喷口组成，在支板火焰稳定器尾部两侧交替布置6～20个梯形凹槽，使得剩余的垂直尾缘形成交替的矩形尾缘，在每个矩形尾缘上布置1～2个燃料喷口。本发明的优点和取得的有益效果为：超燃冲压燃烧室采用该喷孔交替布置的支板火焰稳定器，燃烧更稳定、燃烧速度快、总压损失小。

本发明公开燃气涡轮发动机燃料喷射器。一种用于燃气涡轮发动机的燃料喷射器，该燃料喷射器包括燃料喷射器壳体(10)和伸长燃料管(90、100)，该伸长燃料管由间隔开的接头保持在所述壳体中的适当位置，且包括沿所述接头之间的其长度的至少一部分的起伏管表面(90c)，所述起伏管表面(90c)在所述起伏管表面的一个或多个位置处与设置在所述壳体(10)中的另一表面接触。

本发明公开了一种航空发动机燃烧室、帽罩的声衬孔设计方法及航空发动机，航空发动机燃烧室包括外机匣、内机匣和帽罩，所述外机匣、内机匣和帽罩围成一声衬腔，所述帽罩上设置有若干个声衬孔，所述声衬腔通过所述声衬孔与航空发动机燃烧室的燃烧腔连通。该航空发动机燃烧室通过在帽罩上设置若干个声衬孔，以将燃烧腔与外机匣、内机匣和帽罩之间围成的声衬腔连通，由此形成多孔声衬声阻尼结构，该结构在抑制燃烧腔内的压力振荡的同时，还具有在目标频率范围内较佳的吸声特性，还能够对火焰筒进口的空气进行整流，以缓解燃烧腔内发生振荡燃烧时主燃级气流在主流动方向上大尺度的逆流脉动，减小冲击和噪声。

本发明公布了一种复合材料火焰筒及航空发动机，属于航空发动机技术领域，火焰筒包括金属框架，内环组件和外环组件：金属框架包括火焰筒头部组件、电嘴座支杆、定位销支杆、外环出口组件和内环出口组件：火焰筒头部组件包括环状的头部基体，头部基体与外环出口组件之间通过电嘴座支杆和定位销支杆连接，头部基体与内环出口组件之间通过定位销支杆连接；电嘴座支杆上预设的安装孔内设置有电嘴座；定位销支杆上预设的第六螺孔内设置有定位销螺栓，定位销螺栓用于将火焰筒内环与定位销支杆连接定位，定位销螺栓还用于将火焰筒外环与定位销支杆连接定位。本发明能够解决火焰筒热态下金属材料与非金属复合材料之间的密封不严等问题。

The present application provides a cross fire tube installation/removal apparatus (100) for use with a combustor (25) of a gas turbine engine (10). The cross fire tube installation/removal apparatus (100) includes a cross fire tube assembly (110) having a sleeve (120, 130) with a tube groove (170, 180) therein and a cross fire tube tool (300) having a spring (390) with a spring flange (440). The spring flange (340) is sized to engage the tube groove (170, 180).

A fuel injector for a combustor of a gas turbine engine, the injector comprising a fuel injection device 360. The fuel injection device being described as configured to promote cavitation of the fuel. The fuel injection device including a fuel injection port 362 injecting fuel into the combustor. The fuel injection device preferably including a conduit and preferably includes a flow restriction (369, fig 6) within the conduit for maintaining a local static pressure of the fuel below a vapour pressure of the fuel. The fuel injection device preferably having an internal profile having a first radius of curvature and comprising an inlet profile having a second radius of curvature, the first radius of curvature being less than 10 times greater than the second radius of curvature, or preferably being at least 10 times greater. Figure 3

Proposed are a combustor nozzle, and a combustor and a gas turbine including the combuster nozzle. The combustor nozzle includes a plurality of mixing tubes spraying a mixture fluid of air and fuel into spray holes, a rear plate supporting the mixing tubes at each rear end of the mixing tubes, and a fuel supply part mounted in the rear plate and configured to supply fuel. Each outlet of a portion of the mixing tubes is formed at a position corresponding to the fuel supply part. Therefore, since inclination angles are provided in the mixing tubes adjacent to the fuel supply part in the combustor nozzle of the gas turbine so that each outlet of the mixing tubes is evenly disposed, an empty space between each of the mixing tubes is not formed, so that overheating of each outlet of the mixing tubes due to heat concentration may be prevented.

本发明公开了一种提高单凹腔驻涡燃烧室空间利用率的异形火焰筒构型，包括联焰支板、凹腔前壁、凹腔底壁、凹腔后壁、点火电嘴、壁板、外环筒板、内环平直筒板、内环收敛筒板。本发明火焰筒内形成凹腔值班区、主燃区、中间区、壁式补燃区四个燃烧区。本发明对火焰筒的壁式设计及布置方式，一方面解决驻涡燃烧室空间利用率不足的问题，大幅度缩短燃烧室长度，另一方面形成相对独立低速补燃区，对凹腔及主流的高温燃气二次充分燃烧，并匹配补燃级供油满足更高油气组织需求。除此之外，本发明的火焰筒天然的多区组织燃烧，不仅拓宽高温升燃烧室的高效工作范围，也使其具备天然的低排放组织燃烧潜力。