阅读说明：本技术 一种紧凑型向心涡轮导向器 (Compact centripetal turbine guider ) 是由 常国强 徐夏 王海朋 牛延林 于 2019-08-26 设计创作，主要内容包括：本发明一种紧凑型向心涡轮导向器涉及的是一种用于喷气式发动机的部件,具体是微小型涡喷发动机用的向心涡轮设备。本发明一种紧凑型向心涡轮导向器,具有碗状的机匣,在机匣内设置有圆心处于同一轴心线的圆形的轮毂盘,在轮毂盘和机匣之间设置有多片围绕圆心等角度排列的导流叶片；通过导流叶片将轮毂盘和机匣之间分隔为一个个独立的导流腔,导流腔能够高效、平稳地引导气流通过。轮毂盘的圆心处设置有圆形开口,圆形开口的边缘设置有多个等距排列的紧固孔,轮毂盘能够通过螺栓穿插紧固孔,固定安装在喷气发动机上。本发明微小型紧凑型向心涡轮导向器采用精密铸造一体成型。所述的导流叶片为直纹三维的扭叶片。(The invention discloses a compact centripetal turbine guider, and relates to a component for a jet engine, in particular to centripetal turbine equipment for a micro-miniature turbojet engine. The invention relates to a compact centripetal turbine guider, which is provided with a bowl-shaped casing, wherein a circular hub disc with the circle centers positioned on the same axial lead is arranged in the casing, and a plurality of guide vanes which are arranged around the circle centers at equal angles are arranged between the hub disc and the casing; the guide vanes divide the space between the hub disc and the casing into independent guide cavities, and the guide cavities can efficiently and stably guide airflow to pass through. The circle center of the hub disc is provided with a circular opening, the edge of the circular opening is provided with a plurality of fastening holes which are arranged at equal intervals, and the hub disc can be fixedly installed on the jet engine through the fastening holes which are inserted through bolts. The microminiature compact centripetal turbine guider is integrally formed by precision casting. The guide vane is a straight-line three-dimensional twisted vane.)

1. A compact centripetal turbine vane, characterized by: the fan-shaped air conditioner is provided with a bowl-shaped casing, a circular hub disc with the circle center positioned at the same axial lead is arranged in the casing, and a plurality of guide vanes which are arranged around the circle center at equal angles are arranged between the hub disc and the casing; the guide vanes divide the space between the hub disc and the casing into independent guide cavities, and the guide cavities can efficiently and stably guide airflow to pass through;

The circle center of the hub disc is provided with a circular opening, the edge of the circular opening is provided with a plurality of fastening holes which are arranged at equal intervals, and the hub disc can be fixedly installed on the jet engine through the fastening holes which are inserted through bolts.

2. A compact centripetal turbine vane as claimed in claim 1, wherein: the microminiature compact centripetal turbine guider is integrally formed by precision casting.

3. the compact centripetal turbine guider according to claim 1, wherein the guide vane is a straight-line three-dimensional twisted vane, two side surfaces of the guide vane are both in a Bezier curve shape with a three-medium curve, the guide vane is gradually twisted from a front edge to a rear edge, and the twisting angle is 70-80 degrees.

4. A compact centripetal turbine vane as claimed in claim 1, wherein: the guide vanes are linearly distributed with thick front edges and thin tail edges; the thicknesses of the upper end and the lower end of the front edge of the guide vane are the same, and the thicknesses of the upper end and the lower end of the tail edge of the guide vane are the same.

5. A compact centripetal turbine vane as claimed in claim 1, wherein: the runner wall molded lines of the flow guide cavity between the hub plate and the casing are formed by adopting a three-order Bezier curve, and the change of the area of the runner is gentle and monotonically decreased by adjusting the middle 2 control points.

6. A compact centripetal turbine vane as claimed in claim 1, wherein: the guide vane is generated by two section blade profiles at the root tip in a front edge stacking mode, the section blade profile generation modes are angle distribution and thickness distribution, wherein the inlet and outlet angles of the different section blade profiles are the same, but the distribution modes are different, the blade tip section blade profile angle distribution is rear loading, the blade root section blade profile angle distribution is front loading, the different section blade profiles are completely the same in thickness distribution and are linear distribution with thick front edge and thin tail edge.

Technical Field

The invention discloses a compact centripetal turbine guider, and relates to a component for a jet engine, in particular to centripetal turbine equipment for a micro-miniature turbojet engine.

Background

In a micro turbojet engine, a single turbine stage layout is generally adopted, subject to the constraints of structure, materials and processes. The radial-flow centripetal turbine has the characteristics of simple structure, high single-stage drop pressure ratio, high efficiency under small flow and the like, and is widely applied to the micro turbojet engine. With the increasing performance index of the engine, the size ratio of the turbine part is increased continuously under the condition of meeting enough power. In domestic and foreign published documents, the guide is designed in a pure radial manner, so that the size of the guide is difficult to reduce, and the performance of a turbine part is reduced due to the reduction of the size of the guide, so that a new guide needs to be designed to meet the actual use requirement.

Disclosure of Invention

In view of the above, the invention provides a compact centripetal turbine guider, which has the characteristics of compact structure and high pneumatic efficiency and has good use and popularization values.

The invention relates to a compact centripetal turbine guider, which is provided with a bowl-shaped casing, wherein a circular hub disc with the circle centers positioned on the same axial lead is arranged in the casing, and a plurality of guide vanes which are arranged around the circle centers at equal angles are arranged between the hub disc and the casing; the guide vanes divide the space between the hub disc and the casing into independent guide cavities, and the guide cavities can efficiently and stably guide airflow to pass through.

The circle center of the hub disc is provided with a circular opening, the edge of the circular opening is provided with a plurality of fastening holes which are arranged at equal intervals, and the hub disc can be fixedly installed on the jet engine through the fastening holes which are inserted through bolts.

The microminiature compact centripetal turbine guider is integrally formed by precision casting.

the guide vane is a straight degrees ~ line three degrees ~ dimensional twisted vane, the two side surfaces of the guide vane are in a Bezier curve shape with a three degrees ~ medium curve, the guide vane is gradually twisted from the front edge to the rear edge, and the twisting angle is 70 degrees ~ 80 degrees.

The guide vanes are linearly distributed with thick front edges and thin tail edges; the thicknesses of the upper end and the lower end of the front edge of the guide vane are the same, and the thicknesses of the upper end and the lower end of the tail edge of the guide vane are the same.

Molded lines of the wall surface of a flow channel of a flow guide cavity between a hub plate and a casing are formed by adopting a three-order Bezier curve, and the change of the area of the flow channel is smooth and monotonically decreased by adjusting 2 control points in the middle;

The guide vane is generated by two section blade profiles at the root tip in a front edge stacking mode, the section blade profile generation modes are angle distribution and thickness distribution, wherein the inlet and outlet angles of the different section blade profiles are the same, but the distribution modes are different, the blade tip section blade profile angle distribution is rear loading, the blade root section blade profile angle distribution is front loading, the different section blade profiles are completely the same in thickness distribution and are linear distribution with thick front edge and thin tail edge.

the invention has the beneficial effects that: the problem of turbine part performance reduction caused by guide space shortening in the micro-miniature turbojet engine is solved, the length of the micro-miniature turbojet engine can be effectively shortened, the total pressure recovery coefficient of the guide is improved, the through-flow capacity and efficiency of the turbine part are improved, and the micro-miniature turbojet engine has good use and popularization values.

Drawings

Fig. 1 is a schematic view of a partial cross-sectional structure in a three-dimensional state according to the present invention.

Fig. 2 is a schematic view of the air intake direction of the air flow in the cross-sectional state of the present invention.

Fig. 3 is a schematic perspective view of the present invention.

Fig. 4 is a schematic view of a single guide vane of the present invention.

Detailed Description

the invention is described in further detail below:

The invention relates to a compact centripetal turbine guider, which is provided with a bowl-shaped casing 2, wherein a circular hub disc 1 with the circle center positioned at the same axial lead is arranged in the casing 2, and a plurality of guide vanes 3 which are arranged around the circle center at equal angles are arranged between the hub disc 1 and the casing 2; the guide vanes 3 divide the space between the hub plate 1 and the casing 2 into independent guide cavities, and the guide cavities can efficiently and stably guide airflow to pass through.

The circle center of the hub plate 1 is provided with a circular opening 4, the edge of the circular opening 4 is provided with a plurality of fastening holes 5 which are arranged at equal intervals, and the hub plate 1 can be fixedly installed on the jet engine by inserting the fastening holes 5 through bolts.

The microminiature compact centripetal turbine guider is integrally formed by precision casting.

the guide vane is a straight degrees ~ line three degrees ~ dimensional twisted vane, the two side surfaces of the guide vane are in a Bezier curve shape with a three degrees ~ medium curve, the guide vane is gradually twisted from the front edge to the rear edge, and the twisting angle is 70 degrees ~ 80 degrees.

the guide vanes 3 are linearly distributed with thick front edges and thin tail edges; the thicknesses of the upper end and the lower end of the front edge of the guide vane 3 are the same, and the thicknesses of the upper end and the lower end of the tail edge of the guide vane 3 are the same.

Molded lines of the flow channel wall surface of the flow guide cavity between the hub plate 1 and the casing 2 are formed by adopting a three-order Bezier curve, and the change of the flow channel area is gentle and monotonously reduced by adjusting 2 control points in the middle;

The guide vane 3 is generated by stacking two section blade profiles at the root tip in a front edge stacking mode, the section blade profile generation modes are angle distribution and thickness distribution, wherein the inlet and outlet angles of the different section blade profiles are the same, but the distribution modes are different, the blade tip section blade profile angle distribution is rear loading, the blade root section blade profile angle distribution is front loading, the different section blade profiles are completely the same in thickness distribution and are linear distribution with thick front edge and thin tail edge.