CN217999671U

CN217999671U - Turbomachine, aircraft engine and aircraft

Info

Publication number: CN217999671U
Application number: CN202222250275.3U
Authority: CN
Inventors: 葛宣鸣
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2022-08-24
Filing date: 2022-08-24
Publication date: 2022-12-09
Anticipated expiration: 2032-08-24

Abstract

The utility model provides a turbine, an aero-engine and an aircraft, relating to the field of aerospace; the turbine of the utility model comprises a rotating and static shaft cavity and a static wall surface positioned at one side of the rotating and static shaft cavity, wherein the rotating and static shaft cavity is provided with a shaft cavity inlet for cooling airflow to flow in and a shaft cavity outlet for cooling airflow to flow out; the turbine also comprises a guide plate, the guide plate is fixed on the static wall surface and extends from the inlet of the shaft cavity to the outlet of the shaft cavity, and the guide plate does not block the cooling airflow from flowing along the axial direction of the rotating and static shaft cavity; the aero-engine of the utility model comprises the turbine; the utility model discloses an aircraft includes above-mentioned aeroengine. The utility model discloses a set up the guide plate in turbine commentaries on classics dead axle intracavity, destroy cooling air's whirl core to make the difficult vortex that produces of cooling air, favourable and promotion cooling air's cooling effect.

Description

Turbomachine, aircraft engine and aircraft

Technical Field

The utility model relates to an aerospace's field, in particular to turbine, aeroengine and aircraft.

Background

Turbomachines are important power elements in turbine engines. When the engine works, high-temperature gas sprayed from a combustion chamber of the engine impacts on blades of the turbine to drive the blades of the turbine to rotate to do work. To avoid overheating the turbine as much as possible, a portion of the gas from the compressor is typically introduced into the turbine to cool the turbine.

The present turbine includes a stationary member having a stationary wall and a rotating member rotatable relative to the stationary member, the rotating member having a rotating wall, a rotating shaft cavity being formed between the stationary wall and the rotating wall. The cooling air flow led from the compressor flows into the rotating and static shaft cavity, cools the static part and the rotating part and then discharges the cooled cooling air out of the rotating and static shaft cavity.

The cooling air current is owing to the high-speed circumference of rotating the piece is rotatory and the effect of sheltering from of static piece in the quiet axle chamber of commentaries on classics of turbine, forms one or more swirl in the quiet axle chamber of commentaries on classics easily, and the swirl leads to the air current to flow unsmoothly, and the windage heat heating cooling air current that cooling air current and wall friction produced for the cooling air current is to the cooling effect variation of turbine, and the pressure distribution of cooling air current simultaneously is because the vortex exists and become more inhomogeneous.

SUMMERY OF THE UTILITY MODEL

The to-be-solved technical problem of the utility model is to provide a turbine, aeroengine and aircraft in order to overcome among the prior art defect that cooling air current produced the swirl easily in the quiet axle chamber of commentaries on classics.

The utility model discloses an above-mentioned technical problem is solved through following technical scheme:

in a first aspect, the present application provides a turbine, which adopts the following technical solutions:

a turbine comprises a rotating and static shaft cavity and a static wall surface positioned on one side of the rotating and static shaft cavity, wherein the rotating and static shaft cavity is provided with a shaft cavity inlet for cooling airflow to flow in and a shaft cavity outlet for cooling airflow to flow out; the air conditioner further comprises a guide plate, the guide plate is fixed on the static wall surface and extends from the inlet of the shaft cavity to the outlet of the shaft cavity, and the guide plate does not block the cooling air flow from flowing along the axial direction of the static shaft cavity.

In the scheme, the guide plate extends from the inlet of the shaft cavity to the outlet of the shaft cavity and plays a role in guiding the cooling air flow in the static shaft cavity, so that the air flow smoothly passes through the shaft cavity along the guiding structure, the rotational flow core of the cooling air flow is damaged, and the vortex is not easily formed in the static shaft cavity, therefore, the problems that the cooling air flow is not smooth due to the generation of the vortex, the cooling effect is poor due to the fact that the cooling air flow is heated by wind resistance heat generated by wall surface friction, the cooling effect of the cooling air flow is improved, and the pressure distribution characteristic of the cooling air flow is improved are solved; in addition, the guide plate does not block the cooling airflow from flowing along the axial direction of the rotating shaft cavity, namely the guide plate is not easy to be vertical to the flowing direction of the cooling airflow or an acute angle is formed between the guide plate and the flowing direction of the cooling airflow, so that the guide plate blocks the flowing of the cooling airflow; thereby be difficult for when making the cooling air current to the direction of axle chamber export flow taking place to collide the resilience and form the swirl with the guide plate, further improve the cooling effect and the pressure distribution condition of cooling air current.

Preferably, one end of the guide plate, which is far away from the shaft cavity inlet, is spaced from the stationary wall surface.

In the scheme, one end of the guide plate is fixed on the part of the static wall surface, which is close to the inlet of the axial cavity, and the other end of the guide plate is suspended towards the outlet of the axial cavity and is arranged at intervals with the static wall surface; therefore, the guide plate is not easy to completely divide the rotating shaft cavity into two cavities which are not communicated with each other, so that the area of the flowing part of the cooling air flow in the rotating shaft cavity of the turbine can not be changed while the cooling air flow is guided, and the cooling air flow is ensured to flow in the rotating shaft cavity and dissipate less and have a cooling effect.

Preferably, the baffles are circumferentially arranged in series.

In this scheme, the guide plate axial is arranged in succession to make the guide plate be the coaxial annular member of wearing to establish in the static wall, make the guide plate to the cooling air current homoenergetic water conservancy diversion that gets into along each angle and change the quiet axle chamber from this, make the flow of cooling air current more evenly stable.

Preferably, the extending direction of the guide plate is parallel to the stationary wall surface.

In the scheme, the extending direction of the guide plate is parallel to the static wall surface, and the design mode can enable the outline of the guide plate to be close to the outline of the inner part of the static wall surface, so that the influence of the guide plate on other design parameters in the cavity of the rotating static shaft is reduced; meanwhile, the guide plate is kept parallel to the static wall surface, so that the transition between the guide plate and the static wall surface is smooth, namely, cooling air is not easy to form vortex due to the blocking of the abrupt static wall surface after being guided by the guide plate.

Preferably, the turbine further includes a rotating wall surface located on one side of the rotating and stationary axial cavity, the rotating wall surface is disposed opposite to the stationary wall surface, and the interval between the guide plate and the rotating wall surface gradually increases from the inlet of the axial cavity to the outlet of the axial cavity.

In this scheme, rotate the interval between wall and the static wall and form above-mentioned quiet axle chamber of commentaries on classics, simultaneously through adjusting static wall, guide plate, the relative distance between the rotation wall for the interval between guide plate and the rotation wall is crescent from the axle chamber import department to axle chamber exit, and the guide plate forms the angle of gradually expanding with the rotation wall promptly, thereby makes the cooling air current that flows between rotation wall and the guide plate can flow unobstructed.

Preferably, the guide plate comprises an installation edge and a guide edge, the installation edge is fixed on the static wall surface, the guide edge is connected to the installation edge, and one end, far away from the installation edge, of the guide edge overhangs towards the direction close to the shaft cavity outlet.

In this scheme, the mounting panel is used for fixed mounting in order to support the water conservancy diversion limit and keep away from the static wall on the static wall for there is the interval so that the water conservancy diversion limit changes the flow condition of the interior cooling air current of pivot axle chamber with the static wall between the water conservancy diversion limit.

Preferably, the mounting edge is bolted to the stationary wall surface.

In the scheme, the mounting edge is fixed on the static wall surface through the bolt, and the fixing method is firm and reliable in connection, simple and fast.

Preferably, the length of the guide plate along the axial direction of the rotating and static shaft cavity accounts for 1/2-2/3 of the axial length of the rotating and static shaft cavity.

In the scheme, when the length of the guide plate relative to the rotating and static shaft cavity is too short, the cooling airflow in the partial area of the rotating and static shaft cavity close to the shaft cavity outlet is easy to form vortex due to the fact that the cooling airflow is not guided by the guide plate; when the length of the guide plate relative to the static shaft cavity is too long, the gap between the guide plate and the static wall surface is easy to be too small, so that the two cavities at the two sides of the guide plate are not communicated well, the guide plate consumes more material, and the installation is inconvenient; tests show that the range covered by the guide plate when the axial length of the guide plate along the rotating and static shaft cavity accounts for 1/2-2/3 of the axial length of the rotating and static shaft cavity is wider, and the gap between the guide plate and the static wall surface can ensure that the cavities at the two sides of the guide plate are communicated with each other.

In a second aspect, the present application provides an aircraft engine comprising a turbine as described above, the advantages of which are the same as those of the turbine described above and will not be described here in detail.

In a third aspect, the present application provides an aircraft having a turbine as described above, the advantages of which are the same as those of the turbine and the aircraft engine described above, and are not described in detail here.

The utility model discloses an actively advance the effect and lie in:

the utility model discloses a set up the guide plate that extends from the import of shaft chamber to the export of shaft chamber in the quiet axle chamber of commentaries on classics of turbine, the cooling airflow that gets into the quiet axle chamber of commentaries on classics of shaft chamber import is from the export of shaft chamber after the guide plate water conservancy diversion and changes quiet axle chamber, and the vortex core of cooling air current is destroyed to the guide plate for cooling air current is difficult for generating the swirl when flowing, and then reduces pressure loss and the temperature rise that causes because of cooling air current generation swirl, improves cooling air current's cooling effect, improves pressure distribution characteristic.

Drawings

Fig. 1 is a schematic view of an aircraft according to an embodiment of the present invention.

Fig. 2 is a schematic view of an aircraft engine according to an embodiment of the present invention.

Fig. 3 is a schematic structural view of a rotating shaft cavity and a guide plate according to an embodiment of the present invention.

Fig. 4 is a schematic structural view of a flow guide plate according to an embodiment of the present invention

Fig. 5 is an assembly diagram of the mounting edge and the stator casing according to an embodiment of the present invention.

Fig. 6 is a schematic view of the cooling air flow in the cavity of the rotating shaft without the addition of the guide plate of the present invention.

Fig. 7 is a schematic flow diagram of cooling airflow in the cavity of the rotating shaft and the stationary shaft according to an embodiment of the present invention.

Description of the reference numerals:

static wall 100

Rotating wall 200

Flow guide plate 300

Mounting edge 310

Flanging 311

Flow guiding edge 320

Rotating and static shaft cavity 400

Axial cavity inlet 410

Lumen outlet 420

Rotating cavity 430

Quiet chamber 440

Communication port 450

Stator casing 500

Diffuser 600

Connecting bolt 700

Turbomachine 800

Aircraft engine 900

Detailed Description

The present invention will be more clearly and completely described in the following detailed description of the preferred embodiments in conjunction with the accompanying drawings.

An embodiment of the utility model discloses an aircraft, refer to fig. 1, it includes the aircraft body and is used for providing the aeroengine of drive power for the aircraft body. Wherein the aircraft body is the same as in the related prior art and is not described in detail herein.

Referring to fig. 2, an aircraft engine 900 includes fan blades, a compressor, a combustion chamber, and a turbine 800, among other things. The parts of the fan blade, the air compressor, the combustion chamber and the like are not the same as those in the prior art, can be selected and adjusted according to requirements, and are not described again.

Referring to fig. 2 and 3, a turbine 800 of an embodiment of the present application includes a stationary member, a rotating member, and a baffle 300 disposed between the stationary member and the rotating member. The stationary member has a stationary wall 100, the rotating member has a rotating wall 200 corresponding to the stationary wall 100, and a rotating shaft chamber 400 through which the cooling air flows is enclosed between the stationary wall 100 and the rotating wall 200. One end of the static shaft chamber 400 has a shaft chamber inlet 410 and the other end has a shaft chamber outlet 420. The baffle 300 is secured to the stationary wall 100 and extends from the axial cavity inlet 410 to the axial cavity outlet 420. The cooling air flow can flow into the rotating and static shaft cavity 400 from the shaft cavity inlet 410 and flow out from the shaft cavity outlet 420 after being guided by the guide plate 300.

The baffle 300 does not block the flow of the cooling air flow along the axial direction of the rotating and static shaft cavity 400, that is, the baffle 300 is not easy to form an included angle of not more than 90 degrees with the flow direction of the cooling air flow when extending along the axial direction of the rotating and static shaft cavity 400, so that the flow direction of the cooling air flow is approximately parallel to the extending direction of the baffle 300, and the cooling air flow is not easy to collide with the baffle 300 to rebound to form a vortex when flowing towards the direction of the shaft cavity outlet 420.

Referring to fig. 4, the flow guiding plates 300 are uniformly arranged along the circumferential direction, so that the flow guiding plates 300 are annular members that are sleeved outside the rotating wall surface 200 and penetrate through the stationary wall surface 100. The baffle 300 divides the rotating shaft chamber 400 into a dead chamber 440 adjacent to the stationary wall 100 and a rotating chamber 430 adjacent to the rotating wall 200, and the baffle 300 guides the cooling air flow flowing from various angles to flow along the rotating chamber 430.

Therefore, the guide plate 300 guides the cooling air flow to destroy the rotational flow core of the cooling air flow, so that the static shaft cavity 400 is not easy to form a vortex. Thereby reducing the pressure loss and the windage temperature rise of the cooling air flow when flowing in the static shaft cavity 400 and improving the cooling effect of the cooling air flow.

In this embodiment, the baffle 300 is made of titanium alloy, and other suitable high-temperature and high-strength alloys may be used according to the requirement.

Referring to fig. 3 and 4, the baffle 300 includes a mounting edge 310 and a flow directing edge 320. The mounting edge 310 is used to fixedly attach the stationary wall 100. The flow guiding edge 320 extends along the axial direction of the rotating shaft cavity 400 for guiding the cooling air flow. The flow directing edge 320 is secured to the mounting edge 310 on a side facing the axial cavity outlet 420 such that the mounting edge 310 supports the flow directing edge 320 such that the flow directing edge 320 is spaced from the stationary wall 100. Here, the mounting edge 310 and the flow guiding edge 320 may be connected by welding, bolting, integral molding, etc., and in this embodiment, the mounting edge 310 and the flow guiding edge 320 are integrally manufactured by a metal plate.

Referring to fig. 3 and 5, mounting flange 310 is attached to stationary wall 100 at the end of rotating shaft cavity 400 near shaft cavity entrance 410. The mounting edge 310 and the stationary wall 100 may be fixedly connected by bolts, rivets, welding, or the like. In this embodiment, the stationary wall surface 100 is an inner wall of the stator casing 500, the stator casing 500 is provided with a connecting bolt 700 penetrating through the stator casing 500, the diffuser 600 is fixed to the stator casing 500 through the connecting bolt 700, flanges 311 provided with through holes are arranged on two sides of the mounting edge 310, and a portion of the connecting bolt 700 located in the stator casing 500 penetrates through the through hole of the flange 311 to realize connection between the mounting edge 310 and the stationary wall surface 100. This arrangement allows for better utilization of the existing structure of the turbine 800, reducing additional perforations.

The flow directing edge 320 extends from the cavity inlet 410 to the cavity outlet 420 to direct the cooling airflow. The guiding edge 320 is parallel to the stationary wall 100, i.e. the distances from the points on the guiding plate 300 to the stationary wall 100 are the same. Therefore, the outline of the baffle 300 is close to the outline of the inner part of the static wall surface 100, and the cooling air is not easy to form vortex due to the blocking of the convex static wall surface 100 after being guided by the baffle 300.

The end of the flow guiding edge 320 far away from the shaft cavity inlet 410 is spaced from the stationary wall surface 100, so that an annular communicating opening 450 is formed between the end of the flow guiding edge 320 far away from the shaft cavity inlet 410 and the stationary wall surface 100, and the communicating opening 450 is communicated with the stationary cavity 440 and the rotating cavity 430, so that the area of a cooling air flow flowing part in the rotating and stationary shaft cavity 400 of the turbine 800 is not easily changed while the flow guiding edge 320 guides cooling air flow, and the cooling air flow is ensured to have a cooling effect on the inner wall of the rotating and stationary shaft cavity 400.

The distance between the flow guiding edge 320 and the rotating wall surface 200 gradually increases from the axial cavity inlet 410 to the axial cavity outlet 420, that is, the flow guiding edge 320 is divergent, the small mouth end of the flow guiding edge is close to the axial cavity inlet 410, and the large mouth end of the flow guiding edge is close to the axial cavity outlet 420. Thereby enabling the cooling air flow flowing between the rotating wall surface 200 and the baffle 300 to flow smoothly.

Wherein, the ratio of the length of the flow guide edge 320 along the axial direction of the rotating and static shaft cavity 400 to the axial length of the rotating and static shaft cavity 400 is 1/2-2/3. It is verified that the above length range can make the coverage of the flow guiding edge 320 wider, and at the same time, the circulation of the rotating cavity 430 and the static cavity 440 is ensured, which is beneficial to the flow of the cooling air flow. In addition, in other embodiments, one skilled in the art can select other suitable length ranges to ensure that the overall operation is not affected.

In this embodiment, the cooling airflow flows into the static shaft cavity 400 from the shaft cavity inlet 410, and the guide plate 300 damages the vortex core of the cooling airflow, so that the cooling airflow is not easy to generate vortex when flowing, and the cooling airflow is not easy to cause too large pressure drop due to vortex generation or increase friction due to vortex generation, so that the temperature of the cooling airflow is increased, thereby improving the cooling effect of the cooling airflow and improving the pressure distribution characteristic of the cooling airflow.

Combine figure 6 and figure 7, the contrast has the mobile condition of installing the guide plate additional can to see out, and the production of swirl can effectively be avoided to the guide plate to reduce the windage temperature rise, improve pressure distribution's homogeneity. Through verification, the temperature rise of the cooling airflow and the wall surface caused by the wind resistance heat generated by viscous force is reduced to 1/4 of the original temperature rise; the absolute value of the pressure difference between the inlet and the outlet of the rotating and static shaft cavity 400 is reduced to 1/3 of the original structure.

Although specific embodiments of the present invention have been described above, it will be understood by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and the principles of the present invention, and these changes and modifications are all within the scope of the present invention.

Claims

1. A turbine comprises a rotating and static shaft cavity and a static wall surface positioned on one side of the rotating and static shaft cavity, wherein the rotating and static shaft cavity is provided with a shaft cavity inlet for cooling airflow to flow in and a shaft cavity outlet for cooling airflow to flow out; the cooling device is characterized by further comprising a guide plate, wherein the guide plate is fixed on the static wall surface and extends from the inlet of the shaft cavity to the outlet of the shaft cavity, and the guide plate does not block the axial flow of cooling air flow along the static shaft cavity.

2. The turbine of claim 1 wherein an end of said baffle remote from said axial cavity inlet is spaced from said stationary wall.

3. The turbine of claim 1 wherein said baffles are circumferentially arranged in series.

4. The turbine of claim 1 wherein said baffle extends in a direction parallel to said stationary wall.

5. The turbine of claim 1, further comprising a rotating wall surface on a side of said rotating and stationary shaft cavity, said rotating wall surface being disposed opposite said stationary wall surface, and wherein a spacing between said baffle plate and said rotating wall surface increases from an inlet of said shaft cavity to an outlet of said shaft cavity.

6. The turbine of claim 1 wherein said flow directing plate includes a mounting edge and a flow directing edge, said mounting edge being secured to said stationary wall, said flow directing edge being attached to said mounting edge and an end of said flow directing edge remote from said mounting edge overhanging in a direction toward said shaft cavity outlet.

7. The turbine of claim 6 wherein said mounting edge is bolted to said stationary wall.

8. The turbine of claim 1, wherein the length of the baffle plate in the axial direction of the rotor-stator cavity is 1/2 to 2/3 of the axial length of the rotor-stator cavity.

9. An aircraft engine comprising a turbine as claimed in any one of claims 1 to 8.

10. An aircraft having an aircraft engine according to claim 9.