CN116006279A - Interstage casing assembly, gas turbine engine and supporting method thereof - Google Patents

Abstract

The invention provides an interstage casing assembly, a gas turbine engine and a supporting method thereof. The interstage casing assembly includes: an interstage casing; a mounting section; a bearing seat; the oil supply assembly comprises an oil supply pipeline and a nozzle, and the positions of the oil supply pipeline and the nozzle are adjacent to the bearing seat; the mounting joint is positioned at the rear mounting edge of the interstage casing, and the bearing seat is positioned at the radial inner side of the interstage casing. The interstage casing structure with the mounting section and the bearing seat can effectively achieve the effects of simplifying the structure, reducing the number of parts, reducing weight, improving the thrust-weight ratio and reliability and reducing the assembly difficulty.

Description

Interstage casing assembly, gas turbine engine and supporting method thereof

technical field

The invention relates to the technical field of designing an aero-engine casing structure, and in particular relates to an interstage casing assembly and a gas turbine engine.

Background technique

The structure of an aero-engine is complex, as shown in FIG. 1 , generally including a fan 100 , a low-pressure compressor 200 , a high-pressure compressor 300 , a combustion chamber 400 , a high-pressure turbine 500 , and a low-pressure turbine 600 arranged in sequence around the central axis. The high-pressure turbine 500 uses the first rotor shaft 5001 to connect to the high-pressure compressor 300 for driving; the low-pressure turbine 600 uses the second rotor shaft 6001 to connect to the low-pressure compressor 200 and the fan 100 for driving. The airflow passes through the fan 100, flows through the low-pressure compressor 200 and the high-pressure compressor 300, is pressurized in turn, enters the combustion chamber 400, mixes with fuel to form a high-energy airflow, and enters the high-pressure turbine 500 and low-pressure turbine 600 in turn to drive the engine to work . In order to provide good support for each component, at present, the supporting casings of conventional aero-engines generally include intermediate casings 700, interstage casings 800, and turbine rear casings 900. The intermediate casings 700 are located between the low-pressure compressor 200 and the high-pressure compressor. Between the engine 300, the interstage casing 800 is located between the high-pressure turbine 500 and the low-pressure turbine 600, and the turbine rear casing 900 is located behind the low-pressure turbine 600. There are many structural parts and the structure is relatively complicated.

There are many types of parts, resulting in a high weight of the whole machine, which limits the further improvement of the thrust-to-weight ratio. At the same time, due to the large number of parts and the high requirements for the processing and manufacturing precision of the parts, the reliability of the whole machine is poor, the assembly is difficult, and more costs need to be invested. .

Contents of the invention

It is an object of the present invention to provide an interstage casing assembly.

Another object of the present invention is to provide a gas turbine engine.

Another object of the present invention is to provide a method of supporting a gas turbine engine.

An interstage casing assembly according to one aspect of the present invention is characterized in that it includes: an interstage casing; a mounting joint; a bearing seat; an oil supply assembly, including an oil supply pipeline and a nozzle, the oil supply pipeline and The position of the nozzle is adjacent to the bearing seat; wherein, the installation section is located at the rear mounting edge of the interstage casing, and the bearing seat is located at the radial inner side of the interstage casing.

In one or more specific embodiments of the interstage casing assembly, the installation section includes an auxiliary installation section and a rear installation section, and the auxiliary installation section is radial to the circumference of the rear installation edge of the casing. Symmetrical arrangement.

In one or more specific embodiments of the interstage casing assembly, the oil supply assembly includes multiple rows of the oil supply pipelines and the nozzles, and enlarges the oil supply pipelines and the Nozzle flow.

In one or more specific embodiments of the interstage casing assembly, the extension line of the opening direction of the nozzle and the oil supply pipeline connected to the nozzle are arranged non-perpendicularly and non-overlappingly, and the nozzle has Large bore flow path.

In one or more specific embodiments of the interstage casing assembly, the bearing seat includes a connecting portion and a stopper portion, and the connecting portion extends radially outward from the body of the bearing seat for It is connected with the casing; the stop part extends radially inward from the body of the bearing seat, and is used to stop the axial movement of the bearing carried by the bearing seat.

In one or more specific embodiments of the interstage casing assembly, the bearing seat and the casing are integrally or separately arranged.

In one or more specific embodiments of the interstage casing assembly, the bearing seat is located at a position downstream of the center of the casing in the axial direction, increasing the axial length of the interstage casing assembly.

In one or more specific embodiments of the interstage casing assembly, the interstage casing assembly further includes a first sealing structure and a second sealing structure, which are respectively arranged upstream of the bearing seat, downstream.

In one or more specific embodiments of the interstage casing assembly, the first sealing structure and the second sealing structure include coating seals, honeycomb seals, graphite seal ring seals or brush seals. strict.

A gas turbine engine according to another aspect of the present invention, comprising an interstage casing assembly as described above, a high pressure rotor, a low pressure rotor, a main bearing supporting the high pressure rotor, the low pressure rotor, the The bearing housing supports the main bearing, and the oil supply assembly provides lubricating oil to lubricate and cool the main bearing.

According to another aspect of the present invention, a method for supporting a gas turbine engine includes: setting bearing housings in the interstage casing to provide support for the main bearings supporting the high-pressure rotor and low-pressure rotor of the gas turbine engine; An oil supply assembly is arranged to provide lubrication and cooling for the main bearing; a rear installation section is arranged on the rear installation edge of the interstage casing.

The beneficial effects of the present invention include but are not limited to:

The interstage casing structure with mounting joints and bearing seats can effectively achieve the effects of simplifying the structure, reducing the number of parts, reducing the weight, improving the thrust-to-weight ratio and reliability, and reducing the difficulty of assembly.

Description of drawings

The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments. In the accompanying drawings, the same reference numerals always represent the same features. It should be noted that these The accompanying drawings are only examples, and they are not drawn on the same scale, and should not be taken as limiting the protection scope of the actual claims of the present invention, wherein:

Fig. 1 is the structural representation of the turbine engine of prior art;

2 is a schematic diagram of a method for supporting a gas turbine engine according to an embodiment;

Fig. 3 is a schematic structural view of an interstage casing assembly according to an embodiment;

Fig. 4 is the schematic diagram of the nozzle of an embodiment;

Fig. 5 is a schematic diagram of an installation section of an embodiment;

Fig. 6 is a schematic diagram of an auxiliary installation section according to an embodiment.

Reference signs:

100-fan, 200-low pressure compressor, 300-high pressure compressor, 400-combustion chamber, 500-high pressure turbine, 600-low pressure turbine;

5001-the first rotor shaft, 6001-the second rotor shaft;

700-intermediate casing, 800-interstage casing, 900-turbo rear casing;

1-interstage receiver, 101-rear mounting edge;

2-installation section, 201-rear installation section, 202-auxiliary installation section;

3-bearing seat, 301-connection part, 302-stop part;

4-oil supply assembly, 401-oil supply pipeline, 402-nozzle;

501-the first sealing structure, 502-the second sealing structure.

Detailed ways

Reference will now be made in detail to various embodiments of the present invention, examples of which are illustrated in the accompanying drawings and described below. While the invention will be described in conjunction with exemplary embodiments, it will be appreciated that present description is not intended to limit the invention to those exemplary embodiments. On the contrary, the invention is intended to cover not only the exemplary embodiments but also various alternatives, modifications, equivalents and others, which may be included within the spirit and scope of the invention as defined by the appended claims. implementation plan.

In the ensuing description, orientations or positional relationships indicated by "upstream", "downstream", "axial", "radial", "circumferential", "inner", "outer" or other directional terms are based on the drawings The orientations or positional relationships shown are only for the convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or component must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be construed as a reference to the present invention. limits. Meanwhile, the present application uses specific words to describe the embodiments of the present application. For example, "one embodiment" and/or "an embodiment" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that "an embodiment" or "an embodiment" mentioned twice or more at different positions in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present application may be properly combined.

In order to reduce the parts in the engine, break through the traditional interstage casing structure, open up a new design idea for the interstage casing structure, and design an interstage casing assembly, as shown in Fig. 3 and Fig. 4, in an implementation In the manner, an example of the specific structure of the interstage casing assembly may include: an interstage casing 1 , a mounting section 2 , a bearing seat 3 , and an oil supply assembly 4 . The oil supply assembly 4 includes an oil supply pipeline 401 and a nozzle 402 , and the position of the oil supply pipeline 401 and the nozzle 402 is adjacent to the bearing housing 3 . Wherein, the installation section 2 is located at the rear installation edge 101 of the interstage casing 1 , and the bearing seat 4 is located at the radial inner side of the interstage casing 1 . Setting the interstage casing structure with mounting joints and bearing seats can achieve the effects of simplifying the structure, reducing the number of parts, reducing the weight, improving the thrust-to-weight ratio and the reliability of the whole machine, and reducing the difficulty of assembly.

Referring to FIG. 5 in conjunction with FIG. 6 , in one embodiment, an example of the specific structure of the installation section 2 may include an auxiliary installation section 202 and a rear installation section 201 . The auxiliary installation section 202, as shown in FIG. 6, is symmetrically arranged on the circumferential direction of the rear installation edge 101 of the casing. The rear mounting sections 201 , as shown in FIG. 5 , are evenly distributed in the circumferential direction of the rear mounting edge 101 between the auxiliary mounting sections 202 . The turbine rear casing is canceled, and the installation joint is arranged on the interstage casing, so that the engine thrust rod can be connected through the interstage casing.

Referring to FIG. 3 in conjunction with FIG. 4 , in one embodiment, an example of the specific structure of the oil supply assembly 4 may include multiple rows of oil supply pipelines 401 and the nozzles 402, and enlarge the oil supply pipelines 401 and The flow rate of the nozzle 402. As shown in FIG. 3 , the oil supply pipeline 401 is located on both radially inner and outer sides of the bearing housing 3 . Compared with traditional oil supply pipeline components, this embodiment increases the flow rate and reduces the number of pipelines, realizes multi-section, multi-directional lubrication and cooling, reduces the risk of oil leakage from multiple pipelines, and further reduces the weight of the whole machine and the difficulty of assembly. Improve thrust-to-weight ratio.

As shown in FIG. 4 , in one embodiment, an example of the specific structure of the nozzle 402 may be that the extension line of the opening direction of the nozzle 402 and the oil supply pipeline connected to the nozzle 402 are non-vertical and non-overlapping, that is, the nozzle 402 The angle α between the extension line of the opening direction and the oil supply pipeline connected thereto is greater than 0° and less than 90°, and the nozzle 402 has a large diameter flow path. The nozzle shown in FIG. 4 is only an example of the nozzle 402, and the nozzle 402 may also adopt other forms of structures.

Referring to FIG. 3 , in one embodiment, an example of the specific structure of the bearing seat 3 may include a connecting portion 301 and a stopper portion 302 . The connecting portion 301 extends radially outward from the body of the bearing housing 3 and is used for connecting with the interstage casing 1 . The stop portion 302 extends radially inward from the body of the bearing seat 3 and is used to stop the axial movement of the bearing carried by the bearing seat 3 . A brand-new design of the bearing seat can support the high-pressure turbine rotor and the low-pressure turbine rotor at the same time, reduce the number of parts, reduce the weight of the whole machine and the difficulty of assembly, and improve the thrust-to-weight ratio.

Further, in one embodiment, an example of the specific structure of the bearing seat 3 may also be that the bearing seat 3 and the casing 1 are integrally formed or fixedly connected and installed separately.

Furthermore, in one embodiment, an example of the specific structure of the bearing seat 3 may also be that the bearing seat 3 is located at a position downstream of the center of the casing 1 in the axial direction, increasing the axial length of the interstage casing assembly, and the bearing seat 3 The specific position of 3 is determined according to the center of gravity of the engine and the span of each fulcrum, so as to achieve more stable support for the high-pressure rotor and low-pressure rotor at the same time, achieve higher strength, and improve the overall stability of the engine.

Continuing to refer to FIG. 3 , in one embodiment, an example of the specific structure of the interstage casing assembly may include a first sealing structure 501 and a second sealing structure 502 respectively arranged upstream of the bearing seat 3 , downstream. Further, the first sealing structure 501 and the second sealing structure 502 can be selected from coating sealing, honeycomb sealing, graphite sealing ring sealing or brush sealing. Ensure the tightness of the interstage casing assembly.

The gas turbine engine adopting the above-mentioned interstage casing assembly can cancel the various components in the original structure that have the same effect, which will effectively reduce the weight of the whole machine, help improve the thrust-to-weight ratio and the reliability of the whole machine, and at the same time facilitate Assembly, saving manpower, capital, time and other costs. Specifically, in one embodiment, an example of a specific structure of a gas turbine engine may include the above-mentioned interstage casing assembly, a high-pressure rotor, a low-pressure rotor, and a main bearing. The main bearing supports the high-pressure rotor and the low-pressure rotor, the bearing housing 3 supports the main bearing, and the oil supply assembly 4 provides lubricating oil to lubricate and cool the main bearing. The principle is that the gas turbine engine with the above structure realizes the support of the high-pressure rotor and the low-pressure rotor through the interstage casing assembly, and the rear mounting section and the bearing seat structure are integrated in the interstage casing, which simplifies the engine structure In this way, the above-mentioned effects of effectively reducing the weight of the whole machine, improving the thrust-to-weight ratio and the reliability of the whole machine, being easy to assemble, and saving manpower, capital, time and other costs are achieved.

As can be seen from the above, with reference to Figure 2, an implementation of the method of supporting the gas turbine engine using the interstage casing may be:

A bearing seat is provided in the interstage casing to provide support for the main bearing of the high-pressure rotor and the low-pressure rotor of the gas turbine engine; for example, the bearing seat 3 shown in Figure 3, the main bearing of the gas turbine engine supports the high-pressure rotor and the low-pressure rotor. Seat 3 supports the main bearing.

An oil supply assembly is provided in the interstage casing to provide lubrication and cooling for the main bearing; for example, the oil supply assembly shown in Figure 3 and Figure 4 includes multiple rows of oil supply pipelines 401 and the nozzles 402, and is enlarged The flow rate of the oil supply pipeline 401 and the nozzle 402, the positions of the oil supply pipeline 401 and the nozzle 402 are adjacent to the bearing housing 3, the extension line of the opening direction of the nozzle 402 and the oil supply pipeline connected to the nozzle 402 are not vertical and non-overlapping layout.

Rear installation sections are arranged on the rear installation edge of the interstage casing; for example, the rear installation sections shown in FIG. 5 are evenly distributed in the circumferential direction of the rear installation edge 101 between the auxiliary installation sections 202 .

The beneficial effects of such a support method, as described above, include the support of the high-pressure rotor and the low-pressure rotor through the inter-stage casing assembly, and the integration of the rear mounting section and the bearing seat structure in the inter-stage casing, The structure of the engine is simplified, so that the weight of the whole machine can be effectively reduced, the thrust-to-weight ratio and the reliability of the whole machine can be improved, and at the same time, it is easy to assemble and save manpower, capital, time and other costs.

In summary, the beneficial effects of the interstage casing assembly and the gas turbine engine and its supporting method introduced in the above embodiments include but are not limited to one or a combination of the following:

1. Setting the interstage casing structure with mounting joints and bearing seats can achieve the effects of simplifying the structure, reducing the number of parts, reducing the weight, improving the thrust-to-weight ratio and the reliability of the whole machine, and reducing the difficulty of assembly.

2. Compared with traditional oil supply pipeline components, increasing the flow rate reduces the number of pipelines, reduces the risk of oil leakage from multiple pipelines, further reduces the weight of the whole machine and the difficulty of assembly, and improves the thrust-to-weight ratio.

3. Design a new bearing seat, which can support the high-pressure turbine rotor and the low-pressure turbine rotor at the same time, reduce the number of parts, reduce the weight of the whole machine and the difficulty of assembly, and increase the thrust-to-weight ratio.

4. The gas turbine engine adopting the above-mentioned interstage casing assembly can cancel the various components in the original structure that have the same effect, which will effectively reduce the weight of the whole machine and help improve the thrust-to-weight ratio and the reliability of the whole machine. At the same time, it is easy to assemble, saving manpower, capital, time and other costs.

Although the present invention is disclosed above with preferred embodiments, it is not intended to limit the present invention, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any amendments, equivalent changes and modifications made to the above implementation methods according to the technical essence of the present invention, which do not deviate from the technical solutions of the present invention, all fall within the scope of protection defined by the claims of the present invention.

Claims (11)

1. An interstage casing assembly, characterized in that it comprises: interstage receiver; installation section; bearing seat; The oil supply assembly includes an oil supply pipeline and a nozzle, and the position of the oil supply pipeline and the nozzle is adjacent to the bearing seat; Wherein, the installation section is located at the rear installation edge of the interstage casing, and the bearing seat is located at the radial inner side of the interstage casing. 2. The interstage casing assembly according to claim 1, wherein the installation section includes an auxiliary installation section and a rear installation section, and the auxiliary installation section is radial to the circumference of the rear installation edge of the casing. Symmetrical arrangement. 3. The interstage casing assembly according to claim 1, wherein the oil supply assembly includes multiple rows of the oil supply pipelines and the nozzles, and enlarges the oil supply pipelines and the Nozzle flow. 4. The interstage casing assembly according to claim 1, characterized in that, the extension line of the opening direction of the nozzle and the oil supply pipeline connected to the nozzle are arranged non-perpendicularly and non-overlappingly, and the nozzle has Large bore flow path. 5. The interstage casing assembly according to claim 1, wherein the bearing seat includes a connecting portion and a stopper portion, and the connecting portion extends radially outward from the body of the bearing seat for It is connected with the casing; the stop part extends radially inward from the body of the bearing seat, and is used to stop the axial movement of the bearing carried by the bearing seat. 6 . The interstage casing assembly according to claim 5 , wherein the bearing seat and the casing are integrally or separately arranged. 7 . 7 . The interstage casing assembly according to claim 6 , wherein the bearing seat is located axially downstream of the center of the casing, increasing the axial length of the interstage casing assembly. 8 . 8. The interstage casing assembly according to claim 1, characterized in that, the interstage casing assembly further comprises a first sealing structure and a second sealing structure, which are respectively arranged upstream of the bearing seat, downstream. 9. The interstage casing assembly according to claim 8, wherein the first sealing structure and the second sealing structure comprise coating seals, honeycomb seals, graphite seal ring seals or brush seals. strict. 10. A gas turbine engine, characterized in that it comprises an interstage casing assembly as claimed in any one of claims 1-9, a high-pressure rotor, a low-pressure rotor, and a main bearing, and the main bearing supports the high-pressure rotor, For the low-pressure rotor, the bearing seat supports the main bearing, and the oil supply assembly provides lubricating oil to lubricate and cool the main bearing. 11. A method for supporting a gas turbine engine, comprising: Bearing housings are provided in the interstage casing to provide support for the main bearings supporting the high-pressure rotor and low-pressure rotor of the gas turbine engine; An oil supply assembly is arranged in the interstage casing to provide lubrication and cooling for the main bearing; The rear mounting section is set on the rear mounting edge of the interstage casing.

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