CN116006279A - Interstage casing assembly, gas turbine engine and supporting method thereof - Google Patents
Interstage casing assembly, gas turbine engine and supporting method thereof Download PDFInfo
- Publication number
- CN116006279A CN116006279A CN202111226631.1A CN202111226631A CN116006279A CN 116006279 A CN116006279 A CN 116006279A CN 202111226631 A CN202111226631 A CN 202111226631A CN 116006279 A CN116006279 A CN 116006279A
- Authority
- CN
- China
- Prior art keywords
- interstage casing
- interstage
- oil supply
- assembly
- casing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
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
Technical Field
The invention relates to the technical field of aero-engine casing structures, in particular to an interstage casing assembly and a gas turbine engine.
Background
The aircraft engine has a complex structure, and generally includes 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, which are sequentially arranged around a central axis, as shown in fig. 1. The high-pressure turbine 500 is connected to the high-pressure compressor 300 by a first rotor shaft 5001, and is driven; the low-pressure turbine 600 is connected to the low-pressure compressor 200 and the fan 100 by a second rotor shaft 6001, and is driven. The air flows through the fan 100, flows through the low-pressure compressor 200 and the high-pressure compressor 300, is sequentially pressurized, enters the combustion chamber 400, is mixed with fuel to form high-energy air flow, and sequentially enters the high-pressure turbine 500 and the low-pressure turbine 600 to drive the engine to work. In order to provide good support for each component, currently, a conventional aeroengine supporting casing generally comprises an intermediate casing 700, an interstage casing 800 and a turbine rear casing 900, wherein the intermediate casing 700 is positioned between the low-pressure compressor 200 and the high-pressure compressor 300, the interstage casing 800 is positioned between the high-pressure turbine 500 and the low-pressure turbine 600, the turbine rear casing 900 is positioned behind the low-pressure turbine 600, and the whole structure has more parts and is more complex.
The number of parts is various, so that the weight of the whole machine is high, the pushing weight ratio is limited to be further improved, meanwhile, the reliability of the whole machine is poor due to the fact that the number of the parts is large, the machining and manufacturing precision requirements of the parts are high, the assembly difficulty is high, and more cost is required to be input.
Disclosure of Invention
The invention aims to provide an interstage casing assembly.
It is a further object of the present invention to provide a gas turbine engine.
It is a further object of the present invention to provide a method of supporting a gas turbine engine.
An interstage casing assembly according to an aspect of the present invention is characterized by comprising: 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.
In one or more embodiments of the interstage receiver assembly, the mounting section includes an auxiliary mounting section and a rear mounting section, the auxiliary mounting section being radially symmetrically disposed about a circumferential direction of the rear mounting edge of the receiver.
In one or more embodiments of the interstage casing assembly, the oil supply assembly includes a plurality of rows of the oil supply lines and the nozzles, and increases the flow rates of the oil supply lines and the nozzles.
In one or more embodiments of the interstage casing assembly, the extension line of the opening direction of the nozzle and the oil supply pipeline connected with the nozzle are arranged in a non-vertical and non-coincident mode, and the nozzle is provided with a large-caliber flow path.
In one or more embodiments of the interstage casing assembly, the bearing housing includes a connecting portion and a stop portion, the connecting portion extending radially outward from a body of the bearing housing for connection with the casing; the stop extends radially inward from the body of the bearing housing for stopping axial movement of a bearing carried by the bearing housing.
In one or more embodiments of the interstage casing assembly, the bearing housing is integrally or separately disposed with the casing.
In one or more embodiments of the interstage casing assembly, the bearing seat is located axially downstream of the casing center, 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 comprises a first sealing structure and a second sealing structure, which are respectively arranged at the upstream and downstream of the bearing seat.
In one or more embodiments of the interstage casing assembly, the first seal structure, the second seal structure comprises a coating seal, a honeycomb seal, a graphite seal ring seal, or a brush seal.
According to another aspect of the invention, a gas turbine engine comprises an interstage casing assembly, a high pressure rotor, a low pressure rotor and a main bearing as described above, wherein the main bearing supports the high pressure rotor and the low pressure rotor, the bearing seat supports the main bearing, and the oil supply assembly provides lubricating oil for lubricating and cooling the main bearing.
According to another aspect of the invention, a method of supporting a gas turbine engine includes: providing a bearing seat in the interstage casing to support a main bearing for supporting a high-pressure rotor and a low-pressure rotor of the gas turbine engine; providing an oil supply assembly at the interstage casing to provide lubrication cooling for the main bearing; a rear mounting section is provided at a rear mounting edge of the interstage casing.
The beneficial effects of the invention include, but are not limited to:
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.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the accompanying drawings and embodiments in which like reference numerals refer to like features throughout, it being noted that these drawings are given by way of example only, which are not drawn to scale and should not be construed to limit the true scope of the invention, wherein:
FIG. 1 is a schematic structural view of a prior art turbine engine;
FIG. 2 is a schematic illustration of a method of supporting a gas turbine engine of an embodiment;
FIG. 3 is a schematic view of an interstage casing assembly according to an embodiment;
FIG. 4 is a schematic view of a nozzle according to an embodiment;
FIG. 5 is a schematic view of a mounting section of an embodiment;
FIG. 6 is a schematic view of an auxiliary mounting section of an embodiment.
Reference numerals:
100-fan, 200-low pressure compressor, 300-high pressure compressor, 400-combustion chamber, 500-high pressure turbine, 600-low pressure turbine;
5001-a first rotor shaft, 6001-a second rotor shaft;
700-intermediate casing, 800-interstage casing, 900-turbine rear casing;
1-an interstage casing, 101-a rear mounting edge;
2-mounting section, 201-rear mounting section, 202-auxiliary mounting section;
3-bearing seat, 301-connecting part, 302-stopping part;
4-oil supply assembly, 401-oil supply pipeline, 402-nozzle;
501-a first sealing structure, 502-a second sealing structure.
Detailed Description
Reference will now be made in detail to the various embodiments of the invention, examples of which are illustrated in the accompanying drawings and described below. While the invention will be described in conjunction with the exemplary embodiments, it will be appreciated that the present description is not intended to limit the invention to those exemplary embodiments. On the contrary, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents and other embodiments, which may be included within the spirit and scope of the invention as defined by the appended claims.
In the description that follows, references to orientations or positional relationships "upstream," "downstream," "axial," "radial," "circumferential," "inner," "outer," or other azimuthal terms are based on the orientation or positional relationships shown in the drawings, are merely for convenience in describing the invention and simplifying the description, and do not indicate or imply that the devices or components referred to must have a particular orientation, be configured and operated in a particular orientation, and therefore should not be construed as limiting the invention. Meanwhile, the present application uses specific words to describe embodiments of the present application. Reference to "one embodiment" and/or "an embodiment" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the present application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the present application may be combined as suitable.
In order to reduce parts in the engine, break through the traditional inter-stage casing structure form, open up a new design thought of the inter-stage casing structure, design an inter-stage casing assembly, refer to fig. 3 and fig. 4, in an embodiment, an example of a specific structure of the inter-stage casing assembly may be that includes: the device comprises an interstage casing 1, a mounting joint 2, a bearing seat 3 and an oil supply assembly 4. The oil supply unit 4 includes an oil supply line 401 and a nozzle 402, and the oil supply line 401 and the nozzle 402 are located adjacent to the bearing housing 3. Wherein the mounting section 2 is located at the rear mounting side 101 of the interstage casing 1, and the bearing housing 4 is located radially inward of the interstage casing 1. The interstage casing structure with the mounting section and the bearing seat can achieve the effects of simplifying the structure, reducing the number of parts, reducing weight, improving the thrust-weight ratio and the reliability of the whole machine and reducing the assembly difficulty.
Referring to fig. 5 in conjunction with fig. 6, in one embodiment, an example of a specific structure of the mounting section 2 may be a structure including an auxiliary mounting section 202 and a rear mounting section 201. The auxiliary mounting sections 202 are symmetrically arranged in the circumferential direction of the rear mounting side 101 of the casing as shown in fig. 6. The rear mounting sections 201 are evenly distributed in the circumferential direction of the rear mounting rim 101 between the auxiliary mounting sections 202, as shown in fig. 5. The rear casing of the turbine is omitted, and the mounting section is arranged on the interstage casing, so that the interstage casing can be connected with the engine thrust pull rod.
Referring to fig. 3 and fig. 4, in one embodiment, the oil supply unit 4 may include a plurality of rows of oil supply lines 401 and the nozzles 402, and increase the flow rates of the oil supply lines 401 and the nozzles 402. As shown in fig. 3, the oil supply line 401 is located on both radially inner and outer sides of the bearing housing 3. Compared with the traditional oil supply pipeline assembly, the flow is increased, the pipeline quantity is reduced, multi-section and multi-azimuth lubrication and cooling are realized, the risk of oil leakage of multiple pipelines is reduced, the weight of the whole machine and the assembly difficulty are further reduced, and the thrust-weight ratio is improved.
Referring to fig. 4, in one embodiment, an example of a specific structure of the nozzle 402 may be an arrangement in which an extension line of an opening direction of the nozzle 402 and an oil supply line connected to the nozzle 402 are non-vertically and non-coincident, that is, an angle α between the extension line of the opening direction of the nozzle 402 and the oil supply line connected thereto is greater than 0 ° and less than 90 °, and the nozzle 402 has a large-caliber flow path. The nozzle shown in fig. 4 is provided as an example of the nozzle 402, and the nozzle 402 may take other forms.
Referring to fig. 3, in one embodiment, an example of a specific structure of the bearing housing 3 may include a connection portion 301 and a stopper portion 302. The connection 301 extends radially outwardly from the body of the bearing housing 3 for connection with the interstage casing 1. The stop 302 extends radially inwards from the body of the bearing housing 3 for stopping axial movement of the bearing carried by the bearing housing 3. The novel bearing seat is designed, so that the high-pressure turbine rotor and the low-pressure turbine rotor can be supported simultaneously, the number of parts is reduced, the weight and the assembly difficulty of the whole machine are reduced, and the thrust-weight ratio is improved.
Further, in an embodiment, an example of a specific structure of the bearing seat 3 may also be that the bearing seat 3 and the casing 1 are integrally formed or are fixedly connected and installed for separate installation.
Further, in an embodiment, the specific structure of the bearing seat 3 may be that the bearing seat 3 is located at a position axially downstream of the center of the casing 1, so as to increase the axial length of the interstage casing assembly, and the specific position of the bearing seat 3 is determined according to the center of gravity position and the span of each fulcrum of the whole engine, so that the high-pressure rotor and the low-pressure rotor are stably supported at the same time, the strength is higher, and the overall stability of the engine is improved.
With continued reference to fig. 3, in one embodiment, an example of a specific structure of the interstage casing assembly may further include a first sealing structure 501 and a second sealing structure 502, which are disposed upstream and downstream of the bearing seat 3, respectively. Further, the first sealing structure 501 and the second sealing structure 502 may be a coating seal, a honeycomb seal, a graphite seal ring seal, or a brush seal. The tightness of the interstage casing assembly is ensured.
The gas turbine engine adopting the interstage casing assembly can cancel various parts playing the same role in the original structure, effectively reduce the weight of the whole engine, is beneficial to improving the thrust-weight ratio and the reliability of the whole engine, is easy to assemble, and saves the cost of manpower, funds, time and the like. Specifically, in one embodiment, examples of specific structures of the gas turbine engine may be including the interstage casing assembly, high pressure rotor, low pressure rotor, main bearing as described above. The main bearing supports the high-pressure rotor and the low-pressure rotor, the bearing seat 3 supports the main bearing, and the oil supply assembly 4 supplies lubricating oil to lubricate and cool the main bearing. The principle of the gas turbine engine is that the gas turbine engine with the structure realizes the support of the high-pressure rotor and the low-pressure rotor through the interstage casing assembly, and the interstage casing is integrated with the rear mounting section and the bearing seat structure, so that the engine structure is simplified, the weight of the whole engine is effectively reduced, the thrust-weight ratio and the reliability of the whole engine are improved, meanwhile, the assembly is easy, and the cost of manpower, funds, time and the like is saved.
With reference to FIG. 2, one embodiment of a method for supporting a gas turbine engine using an interstage casing may be:
providing a bearing seat in the interstage casing to support a main bearing for supporting a high-pressure rotor and a low-pressure rotor of the gas turbine engine; for example, a bearing housing 3 shown in fig. 3, the main bearing of the gas turbine engine supports a high-pressure rotor and a low-pressure rotor, and the bearing housing 3 supports the main bearing.
Providing an oil supply assembly at the interstage casing to provide lubrication cooling for the main bearing; for example, the oil supply unit shown in fig. 3 and 4 comprises a plurality of rows of oil supply pipelines 401 and the nozzles 402, and increases the flow rates of the oil supply pipelines 401 and the nozzles 402, wherein the oil supply pipelines 401 and the nozzles 402 are positioned adjacent to the bearing seat 3, and the extension line of the opening direction of the nozzles 402 and the oil supply pipeline connected with the nozzles 402 are arranged in a non-vertical and non-overlapping manner.
A rear mounting section is arranged at the rear mounting edge of the interstage casing; such as the rear mounting section shown in fig. 5, are evenly distributed in the circumferential direction of the rear mounting edge 101 between the auxiliary mounting sections 202.
The supporting method has the beneficial effects that the supporting of the high-pressure rotor and the low-pressure rotor is realized through the interstage casing assembly, the rear mounting section and the bearing seat structure are integrated in the interstage casing, so that the engine structure is simplified, the weight of the whole machine is effectively reduced, the thrust-weight ratio and the reliability of the whole machine are improved, the assembly is easy, and the cost of manpower, funds, time and the like is saved.
In summary, the advantages of the interstage casing assembly and the gas turbine engine and the method of supporting the same described in the above embodiments include, but are not limited to, one or a combination of the following:
1. the interstage casing structure with the mounting section and the bearing seat can achieve the effects of simplifying the structure, reducing the number of parts, reducing weight, improving the thrust-weight ratio and the reliability of the whole machine and reducing the assembly difficulty.
2. Compared with the traditional oil supply pipeline assembly, the flow is increased, the number of pipelines is reduced, the risk of oil leakage of multiple pipelines is reduced, the weight and the assembly difficulty of the whole machine are further reduced, and the thrust-weight ratio is improved.
3. The novel bearing seat is designed, so that the high-pressure turbine rotor and the low-pressure turbine rotor can be supported simultaneously, the number of parts is reduced, the weight and the assembly difficulty of the whole machine are reduced, and the thrust-weight ratio is improved.
4. The gas turbine engine adopting the interstage casing assembly can cancel various parts playing the same role in the original structure, effectively reduce the weight of the whole engine, is beneficial to improving the thrust-weight ratio and the reliability of the whole engine, is easy to assemble, and saves the cost of manpower, funds, time and the like.
While the invention has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the invention, and that variations and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present invention fall within the protection scope defined by the claims of the present invention.
Claims (11)
1. An interstage casing assembly, comprising:
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.
2. The interstage casing assembly of claim 1, wherein the mounting section comprises an auxiliary mounting section and a rear mounting section, the auxiliary mounting section being radially symmetrically arranged in a circumferential direction of the casing rear mounting edge.
3. The interstage casing assembly of claim 1, wherein the oil supply assembly includes a plurality of rows of the oil supply lines and the nozzles and increases flow rates of the oil supply lines and the nozzles.
4. The interstage casing assembly according to claim 1, wherein an extension line of an opening direction of the nozzle and an oil supply line connected to the nozzle are arranged in a non-perpendicular non-overlapping manner, the nozzle having a large-caliber flow path.
5. The interstage casing assembly of claim 1, wherein the bearing housing includes a connection portion and a stop portion, the connection portion extending radially outward from a body of the bearing housing for connection with the casing; the stop extends radially inward from the body of the bearing housing for stopping axial movement of a bearing carried by the bearing housing.
6. The interstage casing assembly of claim 5, wherein the bearing housing is integrally or separately provided with the casing.
7. The interstage casing assembly of claim 6, wherein the bearing seat is located axially downstream of the casing center, increasing an axial length of the interstage casing assembly.
8. The interstage casing assembly of claim 1, further comprising a first seal structure, a second seal structure disposed upstream and downstream of the bearing housing, respectively.
9. The interstage casing assembly of claim 8, wherein the first seal structure, the second seal structure comprises a coating seal, a honeycomb seal, a graphite seal ring seal, or a brush seal.
10. A gas turbine engine comprising an interstage casing assembly according to any of claims 1-9, a high pressure rotor, a low pressure rotor, a main bearing supporting the high pressure rotor, the low pressure rotor, a bearing housing supporting the main bearing, and an oil supply assembly providing lubricating oil to lubricate and cool the main bearing.
11. A method of supporting a gas turbine engine, comprising:
providing a bearing seat in the interstage casing to support a main bearing for supporting a high-pressure rotor and a low-pressure rotor of the gas turbine engine;
providing an oil supply assembly at the interstage casing to provide lubrication cooling for the main bearing;
a rear mounting section is provided at a rear mounting edge of the interstage casing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111226631.1A CN116006279A (en) | 2021-10-21 | 2021-10-21 | Interstage casing assembly, gas turbine engine and supporting method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111226631.1A CN116006279A (en) | 2021-10-21 | 2021-10-21 | Interstage casing assembly, gas turbine engine and supporting method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116006279A true CN116006279A (en) | 2023-04-25 |
Family
ID=86023491
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111226631.1A Pending CN116006279A (en) | 2021-10-21 | 2021-10-21 | Interstage casing assembly, gas turbine engine and supporting method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116006279A (en) |
-
2021
- 2021-10-21 CN CN202111226631.1A patent/CN116006279A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10301960B2 (en) | Shroud assembly for gas turbine engine | |
| US11391172B2 (en) | Piloted retaining plate for a face seal arrangement | |
| US10436065B2 (en) | Resilient bearing mount with integral damper fluid passage for a geared turbofan engine | |
| US9982600B2 (en) | Pre-skewed capture plate | |
| EP2964960B1 (en) | Gas turbine engine centrifugal compressor with seal between two diffuser parts | |
| EP3620608B1 (en) | Bearing assembly with a reduced axial space self-pressurizing damper and corresponding method for maintaining pressure in said damper | |
| US20140069107A1 (en) | Turboprop engine with compressor turbine shroud | |
| US9828867B2 (en) | Bumper for seals in a turbine exhaust case | |
| WO2017204949A1 (en) | Fuel delivery system for a gas turbine engine | |
| US20240011443A1 (en) | Oil recovery device for a turbomachine | |
| US20180045218A1 (en) | Shim for gas turbine engine | |
| CN116006279A (en) | Interstage casing assembly, gas turbine engine and supporting method thereof | |
| US20200141275A1 (en) | Centering spring for gas turbine engine bearing compartment | |
| US11022041B2 (en) | Sensor snubber block for a gas turbine engine | |
| EP3816472A1 (en) | Axially rigid curved beam with squeeze damper | |
| US20140090397A1 (en) | Bleed tube attachment | |
| US11459956B2 (en) | Face seal arrangement with reduced balance ratio | |
| US11313471B2 (en) | Shrouded aircraft engine seal carrier | |
| EP3835606A1 (en) | Curved beam centering spring for a thrust bearing | |
| EP3073060B1 (en) | Seal support structures for turbomachines | |
| US11428120B1 (en) | Damping bracket for a gas turbine engine | |
| US11852031B2 (en) | Conduit bracket for a gas turbine engine | |
| CN114502819B (en) | Turbine nozzle with blade assembly made of ceramic matrix composite through which a metal ventilation circuit passes |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |