Turbine case structure with mainstream fuel gas discharging function

Abstract

The invention provides a turbine casing structure with a mainstream fuel gas discharging function, which belongs to the field of aero-engines and comprises a casing front section, a sealing section is formed at the front end of the casing front section, fuel gas discharging grooves distributed at intervals are axially and forwards formed in the inner side of the rear end of the casing front section, and a plurality of fuel gas discharging holes are formed between the sealing section and the rear end of the casing front section; the sealing section abuts against a heat insulation ring of the front casing, and the gas exhaust hole and the gas exhaust groove jointly form a main stream gas exhaust channel. The rear casing section is provided with a mounting edge which is arranged in the radial direction, mounting holes are formed in the mounting edge, and the turbine casing structure can be fixedly connected with the front casing and the rear casing by penetrating connecting pieces through the mounting holes; the casing middle section is integrated with the casing front section and the casing rear section; a rear guider positioning groove and a front guider positioning groove are formed in the rear casing section and the middle casing section through two protruding rings which are spaced by a preset distance and extend backwards in the axial direction, hooks on the front edge and the rear edge of the turbine guider are inserted into the front guider positioning groove and the rear guider positioning groove respectively, and positioning connection of the turbine guider is achieved.

Description

Technical Field

[0001] This application belongs to the field of aero-engines, and specifically relates to a turbine casing structure with mainstream gas exhaust function. Background Technology

[0002] The turbine casing must withstand high temperatures and internal pressures, and transmit the engine's axial forces, torque, and vibration loads. It is essential not only to select appropriate high-temperature resistant materials to ensure the safe and reliable operation of components at high temperatures, but also to ensure the turbine casing has sufficient rigidity while facilitating assembly; and to ensure good thermal centering between the turbine casing components and good concentricity between the rotor and stator.

[0003] The inner casing of the first-stage guide vane of a certain type of low-pressure turbine, as a supporting component of the low-pressure first-stage guide vane, must not only meet all the above-mentioned design specifications, but also have the functional requirement of discharging the mainstream combustion gas to the gas collecting casing, and then discharging the high-temperature combustion gas to the outside of the engine through the ventilation pipe. The existing turbine casing technology cannot achieve the function of discharging the mainstream combustion gas during the whole engine test. Summary of the Invention

[0004] The purpose of this application is to provide a turbine casing structure with mainstream gas discharge function to solve or mitigate at least one of the problems in the prior art.

[0005] The technical solution of this application is: a turbine casing structure with mainstream gas exhaust function, comprising:

[0006] The front section of the casing has a sealing section at its front end and a gas discharge groove that is axially distributed forward on the inner side of the rear end of the front section of the casing. Multiple gas discharge holes are provided between the sealing section and the rear end of the front section of the casing. The sealing section abuts against the heat insulation ring of the front casing. The gas discharge holes and the gas discharge grooves together form the discharge channel for the main gas.

[0007] The rear section of the casing has a radially arranged mounting edge with mounting holes. A connector passes through these mounting holes and connects the turbine casing to the front and rear casings, thus securing the turbine casing structure to them.

[0008] The middle section of the casing is integrated with the front and rear sections of the casing.

[0009] The rear end of the inner side of the rear section of the casing forms a rear guide positioning groove through two protruding rings that are spaced at a predetermined distance and extend axially backward. The inner front end of the middle section of the casing forms a front guide positioning groove through two protruding rings that are spaced at a predetermined distance and extend axially backward. The front and rear edge hooks of the turbine guide are respectively inserted into the front guide positioning groove and the rear guide positioning groove to realize the positioning connection of the turbine guide.

[0010] In at least one embodiment of this application, the diameter and number of the gas discharge holes are determined based on the engine's overall demand for exhaust flow.

[0011] In at least one embodiment of this application, the ventilation area and number of gas discharge slots are determined by converting them to the same flow area as the gas discharge holes.

[0012] In at least one embodiment of this application, the plurality of gas discharge holes are evenly distributed in the circumferential direction.

[0013] In at least one embodiment of this application, the shape of the gas discharge hole includes circular and elliptical shapes.

[0014] The turbine casing structure with mainstream gas discharge function provided in this application can realize the positioning and connection of the turbine guide vane. It can meet the requirements of low-pressure first-stage guide vane installation and positioning, and at the same time meet the design requirements of mainstream gas being discharged to the outside of the engine during whole engine test. Attached Figure Description

[0015] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0016] Figure 1 This is a schematic diagram of the turbine casing structure of this application.

[0017] Figure 2 This is a schematic diagram of the turbine casing structure installation according to this application. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0019] This application provides a turbine casing structure with mainstream gas discharge function, which can meet the functional requirements of discharging mainstream gas to the outside of the engine during the whole engine test, the installation requirements of the low-pressure turbine first-stage guide vane, and the connection requirements between the stator casings.

[0020] like Figure 1 and Figure 2 As shown, the turbine casing structure 100 with mainstream gas exhaust function provided in this application includes a front section 101, a middle section 102, and a rear section 103, which are integrally connected.

[0021] The rear section 103 of the casing includes a radially arranged mounting edge 1, on which mounting holes 2 are provided. For example, the mounting edge 1 has multiple mounting holes 2, evenly distributed along the engine axis. The front and rear end faces of the mounting edge 1 respectively abut against the mounting edges of the front casing 201 and the rear casing 202. Bolts 203 passing through the mounting holes 2 and the mounting edges of the front and rear casings 201 and 202 ensure a tight fit between the turbine casing 100 and the end faces of the front and rear casings 201, achieving isolation between the main combustion gas and the external environment of the engine. For example, the number of bolts 203 is the same as the number of mounting holes 2, and there are multiple bolts 203.

[0022] The front end of the front section 101 of the casing forms a sealing section 3, and the inner side of the rear end of the front section 101 of the casing has spaced gas discharge grooves 5 distributed axially forward. A gas discharge hole 4 is provided between the sealing section 3 and the rear end of the front section 101 of the casing. In this application, multiple gas discharge holes 4 are usually provided and are evenly distributed in the circumferential direction. For example, the gas discharge hole 4 can be a non-stress concentration shape such as a circular hole or an elliptical hole. The sealing section 3 abuts against the heat insulation ring 204 of the front casing 201, thereby forming a sealing structure with the heat insulation ring 204 of the front casing 201, so that a gas collecting chamber is formed between the turbine casing 100 and the front casing 201, preventing the mainstream gas from flowing into other chambers and protecting other stator components from the influence of high-temperature gas. The mainstream gas is first discharged from the gas discharge grooves 5, then enters the gas collecting chamber along the gas discharge holes 4, and finally flows out from the outlet 206 provided on the front casing 201.

[0023] In a preferred embodiment of this application, the diameter and number of gas exhaust holes 4 are determined based on the overall demand of the engine for exhaust flow, and the ventilation area and number of gas exhaust slots 5 are determined by equal flow area conversion.

[0024] The rear inner rear end of the casing rear section 103 forms a rear guide positioning groove 8 through two axially extending rearward protruding rings spaced at a predetermined distance. The rear guide positioning groove 8 serves as the positioning connection structure for the turbine guide 205, providing fixation and support for the rear edge hook structure of the turbine guide 205. Similarly, the front inner front end of the casing middle section 102 forms a front guide positioning groove 6 through two axially extending rearward protruding rings spaced at a predetermined distance. The front guide positioning groove 6 serves as the positioning connection structure for the turbine guide 205, providing fixation and support for the front edge hook structure of the turbine guide 205. The front and rear edge hooks of the turbine guide 205 are inserted into the double-groove front guide positioning groove 6 and rear guide positioning groove 8, respectively, to achieve the positioning connection of the turbine guide 205.

[0025] The turbine casing structure with mainstream gas discharge function provided in this application can realize the positioning and connection of the turbine guide vane. It can meet the requirements of low-pressure first-stage guide vane installation and positioning, and at the same time meet the design requirements of mainstream gas being discharged to the outside of the engine during whole engine test.

[0026] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A turbine casing structure with mainstream gas exhaust function, characterized in that, include: The front section of the casing has a sealing section at its front end and a gas discharge groove that is axially distributed forward on the inner side of the rear end of the front section of the casing. Multiple gas discharge holes are provided between the sealing section and the rear end of the front section of the casing. The sealing section abuts against the heat insulation ring of the front casing. The gas discharge holes and the gas discharge grooves together form the discharge channel for the main gas. The rear section of the casing has a radially arranged mounting edge with mounting holes. A connector passes through these mounting holes and connects the turbine casing to the front and rear casings, thus securing the turbine casing structure to them. The middle section of the casing is integrated with the front and rear sections of the casing. The rear end of the inner side of the rear section of the casing forms a rear guide positioning groove through two protruding rings that are spaced at a predetermined distance and extend axially backward. The inner front end of the middle section of the casing forms a front guide positioning groove through two protruding rings that are spaced at a predetermined distance and extend axially backward. The front and rear edge hooks of the turbine guide are respectively inserted into the front guide positioning groove and the rear guide positioning groove to realize the positioning connection of the turbine guide.

2. The turbine casing structure with mainstream gas exhaust function as described in claim 1, characterized in that, The diameter and number of the gas exhaust holes are determined based on the engine's overall exhaust flow requirements.

3. The turbine casing structure with mainstream gas exhaust function as described in claim 2, characterized in that, The ventilation area and number of gas exhaust troughs are determined by converting them to have the same flow area as the gas exhaust holes.

4. The turbine casing structure with mainstream gas exhaust function as described in claim 3, characterized in that, The multiple gas discharge holes are evenly distributed in the circumferential direction.

5. The turbine casing structure with mainstream gas exhaust function as described in claim 4, characterized in that, The shape of the gas exhaust port includes circular and elliptical.

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