阅读说明：本技术 一种降低旋转螺栓风阻温升的流通结构 (circulation structure for reducing wind resistance temperature rise of rotary bolt ) 是由 吴小军 李宗超 邱天 张�林 田申 于 2019-10-11 设计创作，主要内容包括：本申请属于航空发动机控制技术领域,具体涉及一种降低旋转螺栓风阻温升的流通结构,包括设置在旋转螺栓两端的集气腔与排气腔,以及连通所述集气腔与排气腔的流道,所述流道包括入口段、过渡段及出口段；所述过渡段的流道方向平行于所述旋转螺栓的旋转轴线,所述入口段自所述集气腔起,沿第一弯曲方向延伸至所述过渡段,所述第一弯曲方向具有与所述气流相对流动方向相同的分量,所述出口段自所述过渡段(32)起,沿第二弯曲方向延伸至所述排气腔,所述第二弯曲方向具有与所述气流相对流动方向相反的分量。本申请有效降低了转转系下旋转螺栓的风阻温升,适用与航空发动机狭小腔室的环境。(The application belongs to the technical field of aero-engine control, and particularly relates to an circulation structure for reducing wind resistance temperature rise of a rotary bolt, which comprises a gas collecting cavity and an exhaust cavity which are arranged at two ends of the rotary bolt, and a flow channel communicated with the gas collecting cavity and the exhaust cavity, wherein the flow channel comprises an inlet section, a transition section and an outlet section, the flow channel direction of the transition section is parallel to the rotation axis of the rotary bolt, the inlet section extends to the transition section from the gas collecting cavity along the bending direction, the bending direction has a component identical to the relative flow direction of air flow, the outlet section extends to the exhaust cavity from the transition section (32) along the second bending direction, and the second bending direction has a component opposite to the relative flow direction of the air flow.)

1, kind of circulation structure that reduces rotatory bolt windage temperature rise, its characterized in that includes:

the gas collecting cavity (1) and the exhaust cavity (2) are arranged at two ends of the rotary bolt, and the runner (3) is communicated with the gas collecting cavity (1) and the exhaust cavity (2), and the runner (3) sequentially comprises an inlet section (31), a transition section (32) and an outlet section (33) from the gas collecting cavity (1) to the exhaust cavity (2);

the gas flow has a gas flow relative flow direction relative to the circumferential rotation direction of the rotary bolt in the gas collection cavity (1);

the flow path direction of the transition section (32) is parallel to the rotation axis of the rotary screw, the inlet section (31) extends from the gas collection chamber (1) to the transition section (32) along the th bending direction, the th bending direction has the same component as the relative flow direction of the gas flow, the outlet section (33) extends from the transition section (32) to the gas discharge chamber (2) along the second bending direction, and the second bending direction has a component opposite to the relative flow direction of the gas flow.

2. Flow structure to reduce the windage temperature rise of a swivel bolt according to claim 1, characterised in that the outlet section (33) has a channel structure converging gradually from the transition section (32) to the exhaust chamber (2).

3. Flow structure for reducing the windage temperature rise of a rotating bolt according to claim 1, characterised in that the flow channel (3) has a plurality of flow channels arranged circumferentially around the rotating bolt.

4. Flow structure to reduce the windage temperature rise of swivel bolts according to claim 1, characterized in that the transition section (32) is rounded off from the inlet section (31).

5. Flow structure to reduce the windage temperature rise of swivel bolts according to claim 1, characterized in that the transition section (32) is rounded off to the outlet section (33).

Technical Field

The application belongs to the technical field of aeroengine design, in particular to kinds of circulation structures that reduce rotatory bolt windage temperature rise.

Background

The aviation engine is complex and precise mechanical products, and has the characteristics of high rotating speed, large thrust, strong reliability and the like, bolt structures mounted on a rotating part commonly exist in the aviation engine, and the bolt structures play a role in stirring and acting on airflow flowing through the bolt structures, so that the on-way temperature rise of the airflow is greatly improved, the cooling of the engine is not facilitated, and the adverse effect on the safety of the engine is caused.

The current common methods for dealing with the wind resistance and temperature rise of the bolt comprise two methods, respectively:

a) designing the shape of the bolt, for example, designing the bolt into a novel shape with low flow resistance, such as water drop formation;

b) the bolt is coated, and the turbulent flow effect of the bolt on the airflow is reduced through the smooth coating surface.

The disadvantages of designing a bolt shape solution include:

a) the processing difficulty of a novel structure with small flow resistance, such as a drop-shaped structure, is very high, so that the problems of high cost, long processing time and the like are caused;

b) when the device is used for transferring systems, the cooling and heating effects are poor.

The technical scheme for cladding the bolt has the following defects:

a) the assembly difficulty is large, the method is difficult to apply in a typical narrow cavity of an aeroengine, and the feasibility is poor;

b) when the device is used for transferring systems, the cooling and heating effects are poor.

Disclosure of Invention

In order to solve at least of the above technical problems, the present application provides flow structures for reducing wind resistance temperature rise of a rotation bolt, including:

the gas collecting cavity and the exhaust cavity are arranged at two ends of the rotary bolt, and the runner is communicated with the gas collecting cavity and the exhaust cavity and sequentially comprises an inlet section, a transition section and an outlet section from the gas collecting cavity to the exhaust cavity;

the air flow has an air flow relative flow direction relative to the circumferential rotation direction of the rotary bolt in the air collection cavity;

the flow passage direction of the transition section is parallel to the rotation axis of the rotary bolt, the inlet section extends from the gas collecting cavity to the transition section along the th bending direction, the th bending direction has the same component with the relative flow direction of the gas flow, the outlet section extends from the transition section to the exhaust cavity along the second bending direction, and the second bending direction has the component opposite to the relative flow direction of the gas flow.

Preferably, the outlet section has a channel structure converging from the transition section towards the exhaust cavity.

Preferably, the flow passage has a plurality of flow passages arranged in a circumferential direction of the rotary bolt.

Preferably, the transition section is in smooth transition with the inlet section.

Preferably, the transition section and the outlet section are in smooth transition.

The structure for reducing the wind resistance temperature rise of the rotary bolt has the following two advantages that is used for effectively reducing the wind resistance temperature rise of the rotary bolt under a rotary system, and secondly, the structure with complex processing technology and complex assembly is not adopted, so that the structure is suitable for the environment of a narrow cavity of an aeroengine.

Drawings

Fig. 1 is a schematic structural diagram of a conventional aircraft engine turning bolt.

FIG. 2 is a schematic flow path diagram of an aircraft engine rotary bolt of the present application.

FIG. 3 is a schematic plan view of an aircraft engine swivel bolt of the present application.

Detailed Description

The embodiments described below with reference to the drawings are exemplary and intended to be illustrative of the present application and not to be construed as limiting the present application.

The application provides kinds of circulation structures that reduce rotatory bolt windage temperature rise, is applicable to and changes the system bolt, is not suitable for to change quiet system bolt.

The term "turner bolt" as used herein refers to a bolt that is mounted to a rotor member and still faces the rotor member, and "turner bolt" refers to a bolt that is mounted to a rotor member and faces a stator member. A typical aircraft engine with a turnbuckle is shown in fig. 1, where the walls are all turned walls.

Using figure 2 as an example, illustrates a rotating tie bolt and a static tie bolt, where the gas flow has a circumferential rotational speed in the gas collection chamber, the bolt has a second circumferential rotational speed, typically greater than the circumferential rotational speed, and where the gas flow has no circumferential rotational speed in the gas collection chamber.

The primary flow direction of the gas flow in the rotor system is circumferential flow, with radial and axial flow being generally small. Because the circumferential speed of the incoming flow is small (the rotational flow ratio is less than 1), the circumferential speed of the bolt is large, the bolt pushes the airflow to do work, and the absolute total temperature of the airflow is increased. That is, the reason why the rotation of the bolt causes the wind resistance temperature rise is: rotating the bolt works on the fluid flowing in its vicinity, causing the absolute total temperature of the airflow to rise. The starting point of the design of the application is not to modify the bolt, but to enable the airflow to circumferentially accelerate before flowing through the bolt by a certain low-loss method so as to reach or exceed the circumferential speed of the bolt, thereby reducing the windage temperature rise of the airflow in the whole process.

It is understood in the art that the swirl ratio, i.e., the ratio of the local air flow circumferential velocity to the rotor wall circumferential velocity, is dimensionless numbers that characterize the relative circumferential movement of the air flow and the rotor wall.

The flow structure for reducing the wind resistance temperature rise of the rotary bolt is shown in fig. 2, wherein a fluid domain is physically shown in the flow structure, and a solid domain is arranged in a blank position. The two-dimensional plan view of the flow channel is shown in fig. 3, in which the shaded portion is a solid structure, the blank portion is a flow channel, and the arrow indicates the flow direction of the fluid relative to the rotating member, i.e., the relative velocity direction. The structure of the application is that the flow channel in figure 1 is improved, and the whole annular channel is changed into a U-shaped channel, namely the flow channel 3, which is used for connecting the gas collecting cavity 1 and the exhaust cavity 2. The U-shaped channel is divided into three sections, and the U-shaped channel sequentially comprises an inlet section 31, a transition section 32 and an outlet section 33 from the air collecting cavity 1 to the exhaust cavity 2;

the gas flow has a gas flow relative flow direction relative to the circumferential rotation direction of the rotary bolt in the gas collecting cavity 1;

the flow path direction of the transition section 32 is parallel to the rotation axis of the rotary bolt, the inlet section 31 extends from the gas collecting chamber 1 to the transition section 32 along the th bending direction, the th bending direction has the same component as the relative flow direction of the gas flow, the outlet section 33 extends from the transition section 32 to the gas discharge chamber 2 along the second bending direction, and the second bending direction has the opposite component to the relative flow direction of the gas flow.

By this measure, the direction of the air flow is changed from a → B → C to a → D → E → F → G, and the structure measure is to add a part of the solid body to the rotor, and the shape of the solid body is controlled by the above.

In alternative embodiments, the outlet section 33 has a channel structure that converges gradually from the transition section 32 towards the exhaust chamber 2.

In alternative embodiments, the flow passage 3 has a plurality of flow passages arranged in a circumferential direction of the rotary bolt.

In alternative embodiments, the transition section 32 is rounded to the inlet section 31.

In alternative embodiments, the transition section 32 is rounded to the outlet section 33.

The schematic diagram of the planar flow path for reducing the temperature rise of the wind resistance is shown in fig. 3, wherein the shaded part is a solid structure, the blank part is a flow channel, and an arrow is the flowing direction of the relative rotating member, namely the relative speed direction. The specific principle is as follows:

a) the inlet section is the stage that the swirl ratio is less than 1, and this section needs to be faced the relative velocity direction of air current, reduces the inlet loss of air current through this kind of mode, reduces the windage power adding volume. Taking the right side view of fig. 2 as an example, the swivel bolt has a counter-clockwise direction of rotation, which is greater than the speed of rotation of the air flow, resulting in an opposite clockwise direction of rotation of the air flow, when the inlet section 31 is bent clockwise from the air collecting chamber 1 in order to receive the air flow, so that the air flow is relatively easily accessible to the inlet section.

b) In the middle section of the flow channel, i.e. the transition section 32, the direction of the flow channel is parallel to the axial direction, and the middle process between the flow channel and the inlet section is smoothly transited, so that the swirl ratio of the air flow is gradually transited to 1. Through slow transition, reduce along the circumferential velocity gradient between journey air current and the rotor spare to reduce the dissipation term by a wide margin, reduce the windage temperature rise.

c) In the rear section of the flow channel, namely the outlet section 33, the flow channel direction is inclined in the opposite direction, and the flow channel is a convergent channel (namely a channel with a gradually reduced flow area), so that the airflow is reversed and expanded to accelerate, the circumferential swirl ratio exceeds 1, the bolt is worked or kept relatively static with the bolt after entering the bolt area (the swirl ratio is reduced due to the fact that radial outward flow can cause the conservation of angular momentum), and the wind resistance temperature rise is further reduced by .

It should be noted that when the swirl ratio is over 1 in the transition from the transition section 32 to the outlet section 33, the swirl ratio at the location where the outlet section 33 connects to the discharge chamber can be controlled to be close to 1 because the radial outflow will be attenuated.

The structure for reducing the wind resistance temperature rise of the rotary bolt has the advantages that the is used for effectively reducing the wind resistance temperature rise of the rotary bolt under a rotary system, and the structure which is complex in machining process and assembly is not used, so that the structure is suitable for the environment of a narrow cavity of an aeroengine.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.