CN209761503U

CN209761503U - Turbine casing integrated with active clearance control device and turbine

Info

Publication number: CN209761503U
Application number: CN201920101953.5U
Authority: CN
Inventors: 高爱琼; 濮睿德
Original assignee: Beijing Nanfang Snecma Turbine Technology Co Ltd
Current assignee: Beijing Nanfang Snecma Turbine Technology Co Ltd
Priority date: 2019-01-22
Filing date: 2019-01-22
Publication date: 2019-12-10
Anticipated expiration: 2029-01-22
Also published as: WO2020151578A1

Abstract

The utility model relates to a turbine casing and turbine of integrated initiative clearance control device can save the required human cost of assembly, and can further promote the cooling effect of casing, and its structure includes casing, intake pipe, gas collecting tank and shunt tubes, casing, intake pipe, gas collecting tank and shunt tubes formula structure as an organic whole; the lower part of the flow dividing pipe is fixedly connected with the casing through a lateral flow cavity, and the flow dividing pipe is communicated with the lateral flow cavity through a plurality of impact cooling holes arranged at intervals; and side flow holes are formed in two side walls of the side flow cavity and used for cooling other parts of the turbine casing. A turbine provided with a turbine casing incorporating an active clearance control device as hereinbefore described. According to the utility model discloses enable cooling efficiency and compare original structure and obtain improvement by a wide margin, can more effectual promotion clearance control's technological effect, and then obtain higher engine work efficiency.

Description

Turbine casing integrated with active clearance control device and turbine

Technical Field

The utility model relates to a turbine machine casket technical field, especially an integrated initiative clearance control device's turbine machine casket and turbine.

Background

The turbine of the aircraft engine in the prior art comprises a casing, guide blades, working blades, a turbine disc and the like. In order to maintain high aerodynamic efficiency of the turbine in various operating conditions, an active clearance control device is typically provided on the casing. The basic principle is that when an engine works, a casing is heated by high-temperature gas of a turbine to expand and deform, the outer ring of the turbine generates radial displacement along with the deformation of the casing, so that the blade tip clearance of a rotor is changed, the deformation of the casing in different working states is controlled by an active clearance control device, the blade tip clearance is always controlled in a reasonable range, and the engine efficiency is improved by the active clearance control device.

Active clearance control devices typically cool the casing by impingement cooling. FIG. 1 is a schematic representation of a prior art active clearance control arrangement for a turbine section of an aircraft engine, with brackets and connections not shown. As shown in fig. 1, the active clearance control device of the turbine part of the prior art aeroengine is composed of an air inlet pipe 1, a gas collecting tank 2, a flow dividing pipe 3 and a casing 4, and a hook 6 is arranged on the lower end surface of the casing 4. The cooling air flow is introduced by a low-pressure compressor or a fan of the engine, enters the gas collecting box 2 from the air inlet pipe 1 and then is distributed to the shunt pipes 3. As shown in fig. 2, the side walls of the manifold 3 (near the casing side) are provided with impingement cooling holes H through which the cooling air flows and impinges on the outer surface of the casing 4 for cooling the casing. The shunt tubes 3 are located at the periphery of the hook structure of the case 4, and the size of the case 4 can be controlled by controlling the temperature at the location of the hooks 6.

The structure of the traditional active clearance control device of the turbine part of the aeroengine is too complex, and the manufacturing cost and the weight of the engine are increased. According to different stages of blades in the casing, the number of the annular shunt pipes required by each engine is different from several to ten. In order to ensure a more uniform cooling distribution of the casing, the cooling air flow usually enters a plurality of circumferentially uniformly distributed air inlets from an annular air inlet duct and enters a plurality of air collecting boxes circumferentially uniformly distributed outside the casing for dividing the cooling air flow into the flow dividing pipes. Thus, each annular shunt tube is also divided into several segments, which are mounted on the header tank by means of connectors. Usually, only one gas collection box is composed of dozens of parts through welding and the like, and both time and labor cost are high. In addition, the number of shunt tubes is large, and the assembly work of the shunt tubes is also quite large. Moreover, the shunt tubes need to be fixed on the casing by means of a bracket 5 and the like, so that the weight and the assembly cost of the engine are increased.

The shunt pipe cools the casing through the impact airflow, so the distance between the impact airflow hole at the bottom of the shunt pipe and the outer surface of the casing determines the cooling effect. In the working process of the engine, the deformation of the casing and the deformation of the shunt pipe are inconsistent due to different temperatures of the casing and the shunt pipe. Therefore, the distance between the shunt pipe and the outer surface of the casing cannot be guaranteed, the cooling effect and the effective clearance control effect are influenced, and the engine efficiency is further influenced.

It is therefore desirable to develop a turbine case incorporating an active clearance control device that overcomes at least one of the above-described technical deficiencies.

SUMMERY OF THE UTILITY MODEL

The utility model discloses an initiative clearance control device structure to current aeroengine turbine part is too complicated, and its assembly cost is high and increased the problem of engine weight, provides a novel turbine casket of integrated initiative clearance control device, can sparingly assemble required human cost to can further promote the cooling effect of casket.

Specifically, the present invention achieves the object in the following manner.

In one aspect, the utility model discloses an integrated active clearance control device's turbine casket includes: the gas collecting device comprises a casing, a gas inlet pipe, a gas collecting box and a flow dividing pipe, wherein the casing, the gas inlet pipe, the gas collecting box and the flow dividing pipe are of an integrated structure; the lower part of the flow dividing pipe is fixedly connected with the casing through a lateral flow cavity, and the flow dividing pipe is communicated with the lateral flow cavity through a plurality of impact cooling holes arranged at intervals; and side flow holes are formed in two side walls of the side flow cavity and used for cooling other parts of the turbine casing.

Preferably, the cross-sectional shape of the side flow cavity perpendicular to the gas flow input direction is "U" shaped.

In another aspect, the present invention further provides a turbine provided with the turbine casing integrated with an active clearance control apparatus as described above.

The turbine casing of the integrated active clearance control device provided by the utility model can be manufactured in a 3D printing mode by adopting an integrated structure, so that the connection between the gas collection box and the flow dividing pipe and between each part of the flow dividing pipe is not needed to be realized by assembling parts such as a plurality of joints; the gas collecting box and the flow dividing pipe are not required to be installed on the casing through a support and other parts. Therefore, a lot of labor, time cost and part weight required for assembly can be saved. In addition, because the shunt pipe and the casing are integral parts, the distance between the air impact holes at the bottom of the shunt pipe and the outer surface of the casing can be kept constant in the working process of the engine. Therefore, the clearance can be effectively controlled, and the engine efficiency can be improved. In addition, the side flow cavity which is further additionally arranged below the flow dividing pipe can effectively cool the part fixedly connected with the casing, and the high-speed airflow flowing out of the side flow hole formed in the side wall of the side flow cavity can further effectively cool the exposed upper surface of the casing for the second time, so that the cooling efficiency is greatly improved compared with that of the original structure, the technical effect of controlling the clearance can be effectively improved, and the working efficiency of the engine is higher.

The present invention provides a turbine having the excellent use effect that the aforementioned improvement can achieve by having a turbine case of an integrated active clearance control device according to one of the aforementioned embodiments.

Drawings

Other objects, advantages and features of the present invention will become more readily apparent to those skilled in the art from the following detailed description.

Fig. 1 shows a schematic diagram of a cooling casing according to the prior art.

Fig. 2 is a schematic structural view of the enlarged position a in fig. 1.

FIG. 3 is a block diagram of a turbine casing incorporating an active clearance control device according to one embodiment of the present disclosure.

Fig. 4 is a schematic structural diagram of fig. 3 after the position B is enlarged.

Detailed Description

DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION

As shown in FIG. 3, the present embodiment provides a new turbine case with integrated active clearance control device, comprising: the air-conditioning system comprises a casing 100, an air inlet pipe 200, a gas collecting box 300 and a flow dividing pipe 400, wherein the casing 100, the air inlet pipe 200, the gas collecting box 300 and the flow dividing pipe 400 are of an integrated structure; the lower part of the shunt tube 400 is fixedly connected with the casing 100 through a lateral flow cavity 500. As shown in FIG. 4, the shunt tubes 400 of FIG. 3 communicate with the side flow cavity 500 through a plurality of spaced impingement cooling holes 410; the lateral flow chamber 500 is not used to connect the side wall of the casing 100, and a lateral flow hole 510 is provided at a side facing the casing 100.

In the use state, cooling air flow is introduced by a low-pressure compressor or a fan of the engine, enters the gas collecting box 300 from the air inlet pipe 200 and then is distributed to the shunt pipes 400. As shown in FIG. 4, the bottom of the manifold 400 (near the casing side) is provided with impingement cooling holes 410 through which the cooling air flows and impinges on the upper surface of the casing 100. The shunt tube 400 is located at the periphery of the hook structure of the casing 100 according to the prior art, and the size of the casing 100 can be controlled by controlling the temperature of the hook positions. After cooling, the cooling air in the bypass duct 400 flows out through the side flow holes 510 to further cool the rest of the turbine case 100 and may be directed into the turbine aft case through an outer ring (not shown) to cool the turbine aft case.

The manufacturing of the turbine casing of the integrated active gap control device may be achieved by additive manufacturing, i.e. 3D printing, the intake pipe 200, the header 300, the shunt pipe 400 all being integrally formed with the casing 100. The assembly parts such as a plurality of joints and the like between the gas collection box 300 and the shunt tubes 400 and between the parts of the shunt tubes 400 are not needed; the header 300 and the shunt tubes 400 no longer need to be mounted to the receiver 100 by brackets or the like. Therefore, a lot of labor, time cost and part weight required for assembly can be saved. In addition, since the bypass duct 400 is an integral part of the barrel 100, the distance between the impingement airflow holes 410 at the bottom of the bypass duct 400 and the outer surface of the barrel 100 can be kept constant during engine operation. Therefore, the clearance can be effectively controlled, and the engine efficiency can be improved.

The present application may be implemented in additive manufacturing, i.e. in 3D printing. The improved turbine casing not only saves various assemblies among all parts of the active clearance control device, but also saves the assemblies of all parts of the active clearance control device and the casing. Thus, labor, time costs and part weight required for mass assembly are saved. Additionally, because the utility model discloses it is integrated with shunt tubes and turbine casket, solved current initiative clearance control device shunt tubes and turbine casket and deformed inconsistent in engine working process, made the unstable problem of impingement cooling hole and casket surface distance. The efficiency of impingement cooling is improved, and clearance control can be effectively performed, thereby improving the efficiency of the engine.

Further, as shown in fig. 4, in one preferred embodiment of the present embodiment, the cross-sectional shape of the side flow cavity 500 perpendicular to the airflow input direction is "U" shaped.

It will be appreciated that the present invention provides a turbine having the excellent utility achieved by the foregoing improvements through a turbine case having an integrated active clearance control device according to one of the foregoing embodiments.

Although exemplary preferred embodiments have been shown and described herein, other embodiments consistent with the principles of the invention may be derived by those skilled in the art, and are considered within the scope of the invention.

Claims

1. A turbine casing integrated with an active clearance control device comprises a casing, an air inlet pipe, a gas collecting tank and a flow dividing pipe, and is characterized in that the casing, the air inlet pipe, the gas collecting tank and the flow dividing pipe are of an integrated structure; the lower part of the flow dividing pipe is fixedly connected with the casing through a lateral flow cavity, and the flow dividing pipe is communicated with the lateral flow cavity through a plurality of impact cooling holes arranged at intervals; and side flow holes are formed in two side walls of the side flow cavity and used for cooling other parts of the turbine casing.

2. The integrated active clearance control device turbine casing of claim 1, wherein a cross-sectional shape of the side flow cavity perpendicular to the airflow input direction is "U" shaped.

3. A turbomachine provided with a turbine casing of an integrated active clearance control device according to any of the preceding claims 1-2.