CN111963484A - High-integration-level diffuser structure for small turbine engine - Google Patents
High-integration-level diffuser structure for small turbine engine Download PDFInfo
- Publication number
- CN111963484A CN111963484A CN202010806100.9A CN202010806100A CN111963484A CN 111963484 A CN111963484 A CN 111963484A CN 202010806100 A CN202010806100 A CN 202010806100A CN 111963484 A CN111963484 A CN 111963484A
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- China
- Prior art keywords
- oil
- diffuser
- adapter
- lubricating oil
- turbine engine
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- 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
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- 239000003921 oil Substances 0.000 claims abstract description 102
- 239000010687 lubricating oil Substances 0.000 claims abstract description 45
- 230000005484 gravity Effects 0.000 claims abstract description 13
- 238000007789 sealing Methods 0.000 claims description 14
- 230000010354 integration Effects 0.000 claims description 8
- 238000009792 diffusion process Methods 0.000 abstract description 8
- 230000001050 lubricating effect Effects 0.000 abstract description 4
- 238000005461 lubrication Methods 0.000 description 9
- 238000001816 cooling Methods 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 4
- 238000005381 potential energy Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
- F04D29/0563—Bearings cartridges
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/06—Lubrication
- F04D29/063—Lubrication specially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention belongs to the technical field of aero-engines, and discloses a high-integration diffuser structure for a small-sized turbine engine, wherein the diffuser is divided into a radial diffuser and an axial diffuser, so that the whole diffuser has the function of medium gas diffusion, a bearing sleeve can realize bearing support, and an oil inlet adapter, a lubricating oil inlet pipeline, the bearing sleeve, a lubricating oil gravity oil return cavity, a lubricating oil return pipeline and an oil return adapter form an independent circulating lubricating oil system of the engine, so that the function of lubricating a bearing is realized, and the high thrust-weight ratio of a long-life mini-type engine is met.
Description
Technical Field
The invention belongs to the technical field of aero-engines, relates to a diffuser structure with medium gas diffusion, bearing support and bearing lubrication functions, is particularly suitable for a long-life engine system limited by compact size, has the functions of diffusion, bearing support and independent circulating lubrication and cooling, can greatly improve the integration level of an engine, reduce the number of parts and simplify the structure, and particularly relates to a high-integration-level diffuser structure for a small-sized turbine engine.
Background
In many micro turbine engines, a centrifugal compressor with high supercharging ratio, simple structure, large stable working range and small length is often adopted, a vane diffuser is generally adopted as a stator part of the compressor, the efficiency is high, the supercharging capacity is strong, and the function of the compressor is that kinetic energy applied to airflow energy by rotation of the centrifugal impeller is converted into pressure potential energy, and high-speed airflow with radial and tangential speeds flowing out of the centrifugal impeller needs to be twisted into pure axial airflow through vanes as much as possible to be supplied to a combustion chamber for combustion.
Meanwhile, the rotor of the turbine engine generally has a high rotating speed, and in order to ensure a high thrust-weight ratio of the engine, the supporting, lubricating and cooling space of the bearing is often compressed, so that how to integrate the bearing supporting and lubricating system into other part structures is very important, and the problem is more prominent particularly for a long-life miniature turbine engine with an independent lubricating and cooling system requirement.
Disclosure of Invention
The invention aims to: the diffuser has the functions of medium gas diffusion, bearing support and bearing lubrication simultaneously by arranging the lubricating oil channel and the gravity oil return cavity on the diffuser, and the high thrust-weight ratio of the long-life miniature engine is met.
The technical scheme adopted by the invention is as follows:
the utility model provides a high integration diffuser structure for small-size turbine engine, includes radial diffuser, the last fixedly connected with axial diffuser of radial diffuser, axial diffuser use horizontal central line to communicate in proper order from the top down as the boundary and be equipped with oil feed adapter, lubricating oil inlet pipe way, bearing sleeve, lubricating oil gravity return oil chamber, lubricating oil return oil pipe way, return oil adapter.
Furthermore, a central hole is formed in the axial diffuser of the shaft, and a bearing seat sleeve is arranged in the central hole.
Furthermore, a plurality of first blades which are uniformly distributed along the axial diffuser are arranged on the outer wall of the axial diffuser.
Furthermore, the bearing sleeve comprises a cylinder body, wherein the cylinder body is sequentially communicated with an upper oil inlet hole, an oil groove, a lower oil inlet hole and an oil leakage hole from top to bottom by taking a transverse central line as a boundary line, the upper oil inlet hole is respectively communicated with an oil inlet pipeline and the oil groove, and the oil leakage hole is communicated with an oil gravity return cavity.
Furthermore, the barrel is connected with the axial diffuser through a connecting screw, and a sealing rubber ring for preventing lubricating oil from leaking is arranged at the joint of the barrel and the axial diffuser.
Further, the junction of oil feed adapter, oil return adapter and axial diffuser prevents the sealing washer that the lubricating oil leaked respectively.
Further, the oil inlet adapter is provided with a sealing groove, a sealing ring is arranged in the sealing groove, and the oil return adapter is consistent with the oil inlet adapter in structure.
Further, wear to be equipped with oil feed adapter, oil return adapter on the radial diffuser, and oil feed adapter and the oil feed pipeline intercommunication of lubricating oil, and oil return adapter and lubricating oil return pipeline intercommunication.
Further, two mounting grooves are circumferentially formed in the axial diffuser, and an oil inlet adapter and an oil return adapter are respectively mounted in the two mounting grooves.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
1. in the invention, the diffuser is divided into a radial diffuser and an axial diffuser, so that the diffuser has the functions of medium gas diffusion, bearing support and bearing lubrication at the same time.
2. In the invention, the lubricating oil inlet channel, the gravity oil return cavity and the lubricating oil return channel are arranged in the axial diffuser, so that a lubricating oil pipeline is not required to be additionally arranged, the number of parts of the engine is reduced, and the function of automatic oil return of lubricating oil is realized.
3. In the invention, the bearing sleeve is internally provided with the shunting flow passage, and the lubricating oil from the lubricating oil inlet passage is shunted to the front bearing and the rear bearing after flowing into the shunting flow passage of the bearing sleeve, thereby realizing the function of sharing one path of circulating lubrication by the two bearings.
4. The invention integrates the functions of air flow speed reduction and diffusion, rotor support, bearing cooling and lubrication, etc. into a whole, can increase the function of the diffuser, and when the diffuser is used for an engine, the diffuser can efficiently utilize space, reduce the number of parts and simplify the structure of the engine.
5. In the invention, the radial diffuser is fixedly connected with the axial diffuser, kinetic energy in the gas flow energy exerted by the rotation of the centrifugal impeller can be converted into pressure potential energy, and high-speed gas flow with radial and tangential speeds flowing out of the centrifugal impeller is twisted into pure axial gas flow through the blades as much as possible for the use of a combustion chamber.
6. According to the radial diffuser positioning device, the oil inlet adapter and the oil return adapter have a circumferential positioning function, and circumferential positioning of the radial diffuser is achieved.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view of a portion of FIG. 1;
FIG. 3 is a right side view of FIG. 1;
FIG. 4 is a schematic view of A-A of FIG. 3;
FIG. 5 is a schematic view of a bearing sleeve construction;
FIG. 6 is a right side view of the radial diffuser;
the labels in the figure are: the lubricating oil device comprises a radial diffuser 1, a second blade 11, a second oil inlet adapter 2, a sealing groove 21, a sealing ring 22, an axial diffuser 3, a lubricating oil inlet pipeline 31, a central hole 32, a bearing sleeve 33, a cylinder 331, an upper oil inlet hole 332, an oil groove 333, a lower oil inlet hole 334, an oil leakage hole 335, a sealing rubber ring 336, a lubricating oil gravity oil return cavity 34, a lubricating oil return pipeline 35, a mounting groove 36, a first blade 37, an oil return adapter 4 and a bearing 5.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Example 1
The utility model provides a high integration diffuser structure for small-size turbine engine, includes radial diffuser 1, and fixedly connected with axial diffuser 3 on the radial diffuser 1, axial diffuser 3 uses horizontal central line to communicate in proper order from the top down as the boundary and is equipped with oil feed adapter 2, lubricating oil inlet pipe 31, bearing seat cover sleeve 33, lubricating oil gravity return oil chamber 34, lubricating oil return oil pipe 35, return oil adapter 4.
Further, the axial diffuser 3 is provided with a central hole 32, and a bearing sleeve 33 is arranged in the central hole 32.
Furthermore, a plurality of first vanes 37 which are uniformly distributed along the first vanes are arranged on the outer wall of the axial diffuser 3.
Further, the bearing sleeve 33 includes a cylinder 331, the cylinder 331 is sequentially communicated with an upper oil inlet hole 332, an oil groove 333, a lower oil inlet hole 334, and an oil leakage hole 335 from top to bottom with a transverse center line as a boundary line, the upper oil inlet hole 332 is respectively communicated with the lubricating oil inlet pipeline 31 and the oil groove 333, the oil leakage hole 335 is communicated with the lubricating oil gravity oil return cavity 34, and the oil leakage hole 335 is communicated with the oil groove 333.
Further, the cylinder 331 is connected to the axial diffuser 3 by a connection screw, and a sealing rubber ring 336 for preventing leakage of lubricant is disposed at a connection position of the cylinder 331 and the axial diffuser 3.
Further, the junction of oil feed adapter 2, oil return adapter 4 and axial diffuser 3 prevents sealing washer 22 that the lubricating oil leaked respectively.
Further, be equipped with seal groove 21 on the oil feed adapter 2, be equipped with sealing washer 22 in the seal groove 21, oil return adapter 4 is unanimous with the structure of oil feed adapter 2.
Further, wear to be equipped with oil feed adapter 2, oil return adapter 4 on the radial diffuser 1, and oil feed adapter 2 and the oil inlet pipeline 31 intercommunication of lubricating oil, and oil return adapter 4 and lubricating oil return pipeline 35 intercommunication.
Further, two mounting grooves 36 are circumferentially arranged on the axial diffuser 3, and an oil inlet adapter 2 and an oil return adapter 4 are respectively arranged in the two mounting grooves 36.
Specifically, the second vane 11 is arranged on one side of the radial diffuser 1, which is in contact with the axial diffuser 3.
Specifically, a bearing 5 is arranged in the sleeve of the bearing 5 seat.
Specifically, oil feed adapter 2, oil return adapter 4 are directly connected with external structure oil tank.
Specifically, the radial diffuser 1 and the axial diffuser 3 are connected by a plurality of screws arranged circumferentially.
In the embodiment, the lubricating oil channel and the gravity oil return cavity are arranged on the axial diffuser 3, so that the whole diffuser has an independent circulating lubrication cooling system, and simultaneously has the functions of medium gas diffusion, bearing 5 support and bearing 5 lubrication, and the high thrust-weight ratio of the long-life miniature engine is met; the lubricating oil pump with the external structure conveys lubricating oil in an oil tank to the oil inlet adapter 2, flows into the lubricating oil inlet pipeline 31 through the oil inlet adapter 2, then sequentially passes through the oil inlet hole and the oil groove 333 and is conveyed to the position of the bearing 5 to lubricate the bearing 5, so that the redundant lubricating oil can take away heat of the bearing 5, then flows out of the gravity oil return cavity through the oil leakage hole 335 under the action of gravity, and is conveyed into the oil tank through the lubricating oil return pipeline 35 to form an independent circulating lubrication system, and because the bearing sleeve 33 is arranged in the central hole 32 of the axial diffuser 3 and the bearing 5 is arranged in the bearing sleeve 33, the bearing sleeve 33 can support the bearing 5; because the radial diffuser 1 and the axial diffuser 3 are connected through a plurality of screws, the radial diffuser 1 and the axial diffuser 3 can convert the speed energy into the pressure energy by utilizing the difference of the same flow cross section areas and the difference of the centrifugal impeller, the flow direction of the airflow is limited by the blades, and the high-speed airflow with the radial and tangential speeds flowing out of the centrifugal impeller is converted into the axial airflow for the use of a combustion chamber.
Specifically, the seal rubber ring 336 and the seal ring 22 can prevent oil leakage.
Specifically, the cross section of the oil inlet adapter 2 and the oil return adapter 4 is circular, so that the oil inlet adapter has a circumferential positioning function.
Specifically, the radial diffuser 1 and the axial diffuser 3 realize gas diffusion.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention.
Claims (9)
1. A high-integration diffuser structure for small turbine engines, comprising a radial diffuser (1), characterized in that: fixedly connected with axial diffuser (3) on radial diffuser (1), axial diffuser (3) use horizontal central line to communicate in proper order from the top down as the boundary and are equipped with oil feed adapter (2), lubricating oil inlet pipe way (31), bearing sleeve (33), lubricating oil gravity return oil chamber (34), lubricating oil return oil pipeline (35), return oil adapter (4).
2. A high integration diffuser structure for a small turbine engine as recited in claim 1, wherein: a central hole (32) is formed in the axial diffuser (3), and a bearing seat sleeve (33) is arranged in the central hole (32).
3. A high integration diffuser structure for a small turbine engine as recited in claim 2, wherein: the outer wall of the axial diffuser (3) is provided with a plurality of first blades (37) which are uniformly distributed along the axial diffuser.
4. A high integration diffuser structure for a small turbine engine as recited in claim 1, wherein: bearing sleeve (33) include barrel (331), barrel (331) use horizontal central line to communicate in proper order from the top down as the boundary line and are equipped with last oilhole (332), oil groove (333), inlet port (334), oil leak hole (335) down, go up oilhole (332) and lubricating oil inlet pipe way (31), oil groove (333) intercommunication respectively, oil leak hole (335) and lubricating oil gravity return oil chamber (34) intercommunication.
5. A high integration diffuser structure for a small turbine engine as recited in claim 3, wherein: the barrel (331) is connected with the axial diffuser (3) through a connecting screw, and a sealing rubber ring (336) for preventing lubricating oil from leaking is arranged at the joint of the barrel (331) and the axial diffuser (3).
6. A high integration diffuser structure for a small turbine engine as recited in claim 1, wherein: and the joints of the oil inlet adapter (2), the oil return adapter (4) and the axial diffuser (3) are respectively provided with a sealing ring (22) for preventing lubricating oil from leaking.
7. A highly integrated diffuser structure for a small turbine engine as claimed in claim 5, wherein: be equipped with seal groove (21) on oil feed adapter (2), be equipped with sealing washer (22) in seal groove (21), oil return adapter (4) are unanimous with the structure of oil feed adapter (2).
8. A highly integrated diffuser structure for a small turbine engine as claimed in claim 6, wherein: wear to be equipped with oil feed adapter (2), oil return adapter (4) on radial diffuser (1), and oil feed adapter (2) and lubricating oil inlet pipe way (31) intercommunication, and oil return adapter (4) and lubricating oil return pipe way (35) intercommunication.
9. A highly integrated diffuser structure for a small turbine engine as claimed in any one of claims 5 to 7, wherein: two mounting grooves (36) are circumferentially arranged on the axial diffuser (3), and an oil inlet adapter (2) and an oil return adapter (4) are respectively arranged in the two mounting grooves (36).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010806100.9A CN111963484A (en) | 2020-08-12 | 2020-08-12 | High-integration-level diffuser structure for small turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010806100.9A CN111963484A (en) | 2020-08-12 | 2020-08-12 | High-integration-level diffuser structure for small turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111963484A true CN111963484A (en) | 2020-11-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010806100.9A Pending CN111963484A (en) | 2020-08-12 | 2020-08-12 | High-integration-level diffuser structure for small turbine engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN111963484A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114607626A (en) * | 2021-08-25 | 2022-06-10 | 北京石头世纪科技股份有限公司 | Fan and cleaning equipment |
| CN115095428A (en) * | 2022-05-31 | 2022-09-23 | 中科航星科技有限公司 | Oil mist lubrication cooling structure suitable for high-efficiency cost ratio engine bearing |
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| JPH0797930A (en) * | 1993-09-28 | 1995-04-11 | Mitsubishi Heavy Ind Ltd | Cooling structure of exhaust turbosupercharge |
| CN101446236A (en) * | 2008-12-30 | 2009-06-03 | 北京航空航天大学 | Lubricating and cooling device of rotor bearing of jet engine of microminiature turbine |
| CN104088702A (en) * | 2014-07-01 | 2014-10-08 | 北京航空航天大学 | Compact micro gas turbine |
| CN204646426U (en) * | 2015-05-04 | 2015-09-16 | 中国南方航空工业(集团)有限公司 | Fuel injection system and motor |
| CN107620638A (en) * | 2017-09-15 | 2018-01-23 | 中国科学院工程热物理研究所 | Suitable for the bearing lubrication cooling system of the short-lived turbojet engine of low cost |
| CN208220902U (en) * | 2018-04-18 | 2018-12-11 | 常州环能涡轮动力股份有限公司 | Turbojet engine and its oil channel structures |
-
2020
- 2020-08-12 CN CN202010806100.9A patent/CN111963484A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0797930A (en) * | 1993-09-28 | 1995-04-11 | Mitsubishi Heavy Ind Ltd | Cooling structure of exhaust turbosupercharge |
| CN101446236A (en) * | 2008-12-30 | 2009-06-03 | 北京航空航天大学 | Lubricating and cooling device of rotor bearing of jet engine of microminiature turbine |
| CN104088702A (en) * | 2014-07-01 | 2014-10-08 | 北京航空航天大学 | Compact micro gas turbine |
| CN204646426U (en) * | 2015-05-04 | 2015-09-16 | 中国南方航空工业(集团)有限公司 | Fuel injection system and motor |
| CN107620638A (en) * | 2017-09-15 | 2018-01-23 | 中国科学院工程热物理研究所 | Suitable for the bearing lubrication cooling system of the short-lived turbojet engine of low cost |
| CN208220902U (en) * | 2018-04-18 | 2018-12-11 | 常州环能涡轮动力股份有限公司 | Turbojet engine and its oil channel structures |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114607626A (en) * | 2021-08-25 | 2022-06-10 | 北京石头世纪科技股份有限公司 | Fan and cleaning equipment |
| US12253090B2 (en) | 2021-08-25 | 2025-03-18 | Beijing Roborock Technology Co., Ltd. | Fan and cleaning device |
| CN115095428A (en) * | 2022-05-31 | 2022-09-23 | 中科航星科技有限公司 | Oil mist lubrication cooling structure suitable for high-efficiency cost ratio engine bearing |
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Application publication date: 20201120 |