CN113090392A - Oil return and ventilation structure for transmission of aircraft engine accessories - Google Patents
Oil return and ventilation structure for transmission of aircraft engine accessories Download PDFInfo
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- CN113090392A CN113090392A CN202110526653.3A CN202110526653A CN113090392A CN 113090392 A CN113090392 A CN 113090392A CN 202110526653 A CN202110526653 A CN 202110526653A CN 113090392 A CN113090392 A CN 113090392A
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- cavity
- bearing cavity
- bearing
- oil return
- support plate
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- General Details Of Gearings (AREA)
Abstract
The invention discloses an oil return and ventilation structure for aircraft engine accessory transmission, which comprises a bearing cavity A, wherein one end of the bearing cavity A is provided with a bearing cavity B, a hollow pull rod is arranged on the bearing cavity A and is communicated with the bearing cavity B, an accessory transmission cavity F is arranged above the bearing cavity A, the bearing cavity A and the bearing cavity B are front and rear bearing cavities of a gas generator rotor, the bearing cavity A is connected with the accessory transmission cavity F by adopting a hollow support plate, a centrifugal ventilation device is arranged on the accessory transmission cavity F and is communicated with the atmosphere, a lubricating oil tank ventilation opening is arranged on the accessory transmission cavity F, an oil return pipeline A is arranged on the bearing cavity A, an oil return pipeline B is arranged on the bearing cavity B, and the oil return pipeline A and the oil return pipeline B are both connected with an oil pump, the structure of the engine is compact; the number of parts of the engine rotor is reduced, the weight of the engine is reduced, and the reliability is improved.
Description
Technical Field
The invention belongs to the technical field of turboshaft engines, and particularly relates to an oil return and ventilation structure for transmission of accessories of an aero-engine.
Background
Aircraft engine oil ventilation has been gradually transitioned through a pure external pipe phase to a phase dominated by internal + external pipes. For example, ventilation systems of domestic turboprop-6 engines, turboprop-9 engines, turboshaft-8 engines and foreign VK2500 engines mainly use external pipelines, and a small amount of internal pipelines are adopted for ventilation at positions where casting of a casing is not difficult; with the improvement of casting technology, the proportion of internal pipelines of ventilation systems of 3 rd generation engines such as domestic turboshaft-16 engines, foreign PT6B-67A engines and the like is obviously improved, but external ventilation pipelines are still adopted in chambers of high-temperature parts, and ventilation and oil return of bearing cavities are two independent paths; with the further improvement of the casting technology, external ventilation pipelines are basically omitted for domestic large turboprop engines, foreign RTM322 engines, PT6C-67A engines, T700 engines and the like, and most of the engines adopt oil pump suction for ventilation. In these engines, the ventilation and oil return directions are the same regardless of the ventilation method.
The prior aeroengine lubricating oil ventilation has the following defects:
1. the bearing cavity B is directly ventilated to the accessory transmission cavity F, an external pipeline needs to be added, and the temperature rise of the accessory transmission cavity is increased.
2. The contradiction that the ventilation of the bearing cavity A to the accessory transmission cavity F and the gravity oil return of the accessory transmission cavity F to the opposite flow direction of the bearing cavity A cannot be solved.
Disclosure of Invention
The invention aims to provide an oil return and ventilation structure for the accessory transmission of an aero-engine, which can realize the ventilation from a bearing cavity B to an accessory transmission cavity F through the bearing cavity A, solve the problem that lubricating oil gravity of the accessory transmission cavity F returns to the bearing cavity A, ensure the normal work of a lubricating oil system, reduce the complexity of a pipeline system of the engine, lighten the weight of the engine and have good expansibility.
The purpose of the invention can be realized by the following technical scheme:
an oil return and ventilation structure for accessory transmission of an aircraft engine comprises a bearing cavity A, wherein a bearing cavity B is arranged at one end of the bearing cavity A, a hollow pull rod communicated with the bearing cavity B is arranged on the bearing cavity A, an accessory transmission cavity F is arranged above the bearing cavity A, the bearing cavity A and the bearing cavity B are front and rear bearing cavities of a gas generator rotor, and the bearing cavity A and the bearing cavity B are coaxially arranged; the bearing cavity A is connected with the accessory transmission cavity F through a hollow support plate, a centrifugal ventilation device is arranged on the accessory transmission cavity F and communicated with the atmosphere, a lubricating oil tank ventilation opening is arranged on the accessory transmission cavity F and communicated with a lubricating oil tank, and a lubricating oil pump is connected to the lubricating oil tank; and an oil return pipeline A is arranged on the bearing cavity A, an oil return pipeline B is arranged on the bearing cavity B, and the oil return pipeline A and the oil return pipeline B are both connected with the lubricating oil pump.
As a further scheme of the invention: the sealing device adopted by the rotor in the bearing cavity A is sealed by using medium-pressure air, and the sealing device adopted by the rotor in the bearing cavity B is sealed by using high-pressure high-temperature air, and is decompressed by using a labyrinth and the like.
As a further scheme of the invention: when bearing chamber A and bearing chamber B and not communicate, the pressure in the bearing chamber B is 15 ~ 9100kpa higher than the pressure in the bearing chamber A.
As a further scheme of the invention: the hollow support plate comprises a support plate C, a support plate D and a support plate E, and the support plate C, the support plate D and the support plate E are communicated with the bearing cavity A and the accessory transmission cavity F.
As a further scheme of the invention: and lubricating oil in the accessory transmission cavity F returns to the bearing cavity A through gravity, and the support plate D and the support plate E are used as oil return channels for gravity oil return.
As a further scheme of the invention: and the cavity pressure of the bearing cavity A is lower than the cavity pressure of the accessory transmission cavity F or the cavity pressure of the bearing cavity A is lower than the cavity pressure of the sum of the accessory transmission cavity F and 5 KPa.
As a further scheme of the invention: the support plate D and the support plate E are arranged at included angles with the support plate C, and the positions of the lower port and the upper port of the support plate C are higher than those of the support plate D and the support plate E.
As a further scheme of the invention: and a throttling hole is formed in the hollow pull rod and used for reducing the ventilation volume and the heat quantity of the bearing cavity B to the accessory transmission cavity F through the bearing cavity A.
The invention has the beneficial effects that:
1) an external ventilation pipeline of a cavity B of the bearing cavity is omitted, so that the integration degree of the engine is improved, and the compact structure of the engine is facilitated;
2) the number of parts of the engine rotor is reduced, the weight of the engine is reduced, and the reliability is improved;
3) the cost of the engine is reduced;
4) the invention can realize ventilation from the bearing cavity B to the accessory transmission cavity F through the bearing cavity A, can solve the problem that lubricating oil gravity of the accessory transmission cavity F returns to the bearing cavity A, ensures the normal work of a lubricating oil system, reduces the complexity of an engine pipeline system and lightens the weight of an engine, and has good expansibility.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the connection structure of the bearing cavity A and the accessory drive cavity F of the present invention.
In the figure: 1. a bearing cavity A; 2. a bearing cavity B; 3. an accessory drive cavity F; 4. sealing by medium pressure air; 5. sealing with high-temperature air; 6. a support plate C; 7. a support plate D; 8. a support plate E; 9. a centrifugal ventilation device; 10. a lubricant tank vent; 11. an oil return pipeline A; 12. an oil return pipeline B; 13. a hollow pull rod.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-2, an oil return and ventilation structure for aircraft engine accessory transmission includes a bearing cavity a1, a bearing cavity B2 is disposed at one end of the bearing cavity a1, a hollow pull rod 13 is disposed on the bearing cavity a1 and is communicated with the bearing cavity B2, an accessory transmission cavity F3 is disposed above the bearing cavity a1, the bearing cavity a1 and the bearing cavity B2 are front and rear bearing cavities of a gas generator rotor, and the bearing cavity a1 and the bearing cavity B2 are coaxially disposed; the bearing cavity A1 is connected with the accessory transmission cavity F3 by a hollow support plate, the accessory transmission cavity F3 is provided with a centrifugal ventilation device 9 communicated with the atmosphere, the accessory transmission cavity F3 is provided with a lubricating oil tank ventilation opening 10, the lubricating oil tank ventilation opening 10 is communicated with a lubricating oil tank, and the lubricating oil tank is connected with a lubricating oil pump; an oil return pipeline A11 is arranged on the bearing cavity A1, an oil return pipeline B12 is arranged on the bearing cavity B2, the oil return pipeline A11 and the oil return pipeline B12 are both connected with an oil lubricating pump, the oil lubricating pump sucks lubricating oil in the bearing cavity A1 and the bearing cavity B2 through the oil return pipeline A11 and the oil return pipeline B12 and takes away a part of air in the bearing cavity to increase the pressure of the oil lubricating tank, and the oil lubricating tank is ventilated with an accessory transmission cavity F3 through an oil lubricating tank ventilation opening 10.
The sealing device adopted by the rotor in the bearing cavity A1 uses a medium-pressure air seal 4, and the sealing device adopted by the rotor in the bearing cavity B2 uses a high-temperature air seal 5. After the pressure of the bearing cavity A1 and the pressure of the bearing cavity B2 are relieved and are not communicated, the pressure in the bearing cavity B2 is 15-9100 kpa higher than the pressure in the bearing cavity A1. Between the high pressure bearing chamber B2 and the medium pressure bearing chamber a1, ventilation is provided by means of a hollow tie rod 13 inside the gas generator rotor.
The hollow support plate comprises a support plate C6, a support plate D7 and a support plate E8, and the support plate C6, the support plate D7 and the support plate E8 are communicated with a bearing cavity A1 and an accessory transmission cavity F3; the hollow plate D7 and the plate E8 can be combined into one plate according to the requirement.
The lubricating oil of the accessory transmission cavity F3 returns to the bearing cavity A1 through gravity, and the support plate D7 and the support plate E8 are used as oil return passages for gravity oil return. Air from bearing cavity a1, except for a portion drawn by the lube pump, enters accessory drive cavity F3 mostly through bracket C6 and a small portion may enter accessory drive cavity F3 through bracket D7 and bracket E8.
Based on the pressure of the accessory drive cavity F3, the cavity pressure of the bearing cavity A1 is lower than the sum of the accessory drive cavity F3 cavity pressure +5 kPa.
The inlet at the lower end and the outlet at the upper end of the support plate C6 are higher than the positions of the lower port and the upper port of the support plate D7 and the support plate E8, lubricating oil is returned to the bearing cavity A1 through the gravity of the support plate D7 and the support plate E8 by utilizing the height difference, high-temperature oil gas passes through the support plate C6, the support plate D7 and the support plate E8, and the ice prevention of the support plate can be realized. In the accessory transmission cavity F3, oil return openings of the support plate D7 and the support plate E8 are low, and gravity oil return is relatively facilitated when a special-shaped structure with unequal diameters and equal areas is adopted.
An orifice is provided in the hollow pull rod 13 to reduce the amount of ventilation and heat from the bearing cavity B2 to the accessory drive cavity F3 through the bearing cavity a1 and to reduce the pressure differential between the bearing cavity a1 and the accessory drive cavity F3. The pressure differential between bearing chamber a1 and accessory drive chamber F3 can be adjusted by increasing the capacity of the oil return pump, in conjunction with the path of plate C6, plate D7, and plate E8. In the attitude, the support plate D7 or the support plate E8 has the capacity of realizing the gravity oil return of lubricating oil in the accessory transmission cavity F3.
When the high-pressure gas generator rotor is used, the rotor at the position of the bearing cavity A1 is provided with a sealing device, medium-pressure air sealing 4 is used, the rotor at the position of the bearing cavity B2 is provided with a sealing device, high-temperature air sealing 5 is used, and ventilation is performed between the high-pressure bearing cavity B2 and the low-pressure bearing cavity A1 through a hollow pull rod 13 in the gas generator rotor. The bearing cavity A1 and the accessory transmission cavity F3 are connected by a hollow support plate C6, a support plate D7 and a support plate E8. The accessory transmission cavity F3 is communicated with the atmosphere through a centrifugal ventilation device 9, and a lubricating oil tank ventilation opening 10 is arranged on the accessory transmission cavity F3. An oil return pipeline A11 is arranged on the bearing cavity A1, an oil return pipeline B12 is arranged on the bearing cavity B2, the lubricating oil pump sucks lubricating oil in the bearing cavity A1 and the bearing cavity B2 through the oil return pipeline A11 and the oil return pipeline B12, a part of air in the bearing cavity is taken away, the pressure of the lubricating oil tank is increased, and the lubricating oil tank is ventilated with the accessory transmission cavity F3 through a ventilating opening 10 of the lubricating oil tank. The structure can realize ventilation of the rear bearing cavity B2 of the gas generator rotor to the accessory transmission cavity F3 through the front bearing cavity A1 and realize gravity oil return of lubricating oil of the accessory transmission cavity F3 to the front bearing cavity A1 of the gas generator rotor.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (8)
1. The oil return and ventilation structure for the accessory transmission of the aero-engine is characterized by comprising a bearing cavity A (1), wherein a bearing cavity B (2) is arranged at one end of the bearing cavity A (1), a hollow pull rod (13) communicated with the bearing cavity B (2) is arranged on the bearing cavity A (1), an accessory transmission cavity F (3) is arranged above the bearing cavity A (1), the bearing cavity A (1) and the bearing cavity B (2) are front and rear bearing cavities of a rotor of a gas generator, and the bearing cavity A (1) and the bearing cavity B (2) are coaxially arranged; the bearing cavity A (1) is connected with the accessory transmission cavity F (3) through a hollow support plate, a centrifugal ventilation device (9) is arranged on the accessory transmission cavity F (3) and communicated with the atmosphere, a lubricating oil tank ventilation opening (10) is arranged on the accessory transmission cavity F (3), the lubricating oil tank ventilation opening (10) is communicated with a lubricating oil tank, and the lubricating oil tank is connected with a lubricating oil pump; an oil return pipeline A (11) is arranged on the bearing cavity A (1), an oil return pipeline B (12) is arranged on the bearing cavity B (2), and the oil return pipeline A (11) and the oil return pipeline B (12) are both connected with the lubricating oil pump.
2. The oil return and ventilation structure for the accessory transmission of the aero-engine as claimed in claim 1, wherein the sealing device adopted by the rotor of the bearing cavity A (1) uses a medium-pressure air seal (4), and the sealing device adopted by the rotor of the bearing cavity B (2) uses a high-pressure high-temperature air seal (5).
3. The oil return and ventilation structure for the accessory transmission of the aircraft engine as claimed in claim 2, wherein when the bearing cavity A (1) and the bearing cavity B (2) are not communicated, the pressure in the bearing cavity B (2) is 15-9100 kpa higher than the pressure in the bearing cavity A (1).
4. An oil return and ventilation structure for an aircraft engine accessory drive according to claim 1, wherein the hollow struts include strut C (6), strut D (7) and strut E (8), the struts C (6), D (7) and E (8) communicating the bearing chamber a (1) and the accessory drive chamber F (3).
5. An oil return and ventilation structure for an aircraft engine accessory drive according to claim 4, characterized in that the lubricating oil of the accessory drive chamber F (3) returns to the bearing chamber A (1) by gravity, and the support plate D (7) and the support plate E (8) are used as oil return passages for gravity oil return.
6. The oil return and ventilation structure for an aircraft engine accessory transmission according to claim 1, wherein the cavity pressure of the bearing cavity a (1) is lower than the cavity pressure of the accessory transmission cavity F (3) or the cavity pressure of the bearing cavity a (1) is lower than the cavity pressure of the sum of the accessory transmission cavities F (3) and 5 KPa.
7. The oil return and ventilation structure for the accessory transmission of the aircraft engine as claimed in claim 4, wherein the support plate D (7), the support plate E (8) and the support plate C (6) are arranged at an included angle, and the positions of the lower port and the upper port of the support plate C (6) are higher than those of the support plate D (7) and the support plate E (8).
8. Oil return and ventilation arrangement for an aircraft engine accessory drive according to claim 1, characterized in that an orifice is provided in the hollow tie rod (13) for reducing the amount of ventilation and heat from the bearing cavity B (2) through the bearing cavity a (1) to the accessory drive cavity F (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110526653.3A CN113090392B (en) | 2021-05-14 | 2021-05-14 | Oil return and ventilation structure for transmission of aircraft engine accessories |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110526653.3A CN113090392B (en) | 2021-05-14 | 2021-05-14 | Oil return and ventilation structure for transmission of aircraft engine accessories |
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| Publication Number | Publication Date |
|---|---|
| CN113090392A true CN113090392A (en) | 2021-07-09 |
| CN113090392B CN113090392B (en) | 2022-01-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110526653.3A Active CN113090392B (en) | 2021-05-14 | 2021-05-14 | Oil return and ventilation structure for transmission of aircraft engine accessories |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113530680A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Aviation turboshaft engine lubricating oil system and aviation turboshaft engine |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103982302A (en) * | 2014-05-23 | 2014-08-13 | 中国航空动力机械研究所 | Gas turbine generator set and cooling mechanism used for gas turbine generator set |
| CN104989531A (en) * | 2015-06-23 | 2015-10-21 | 中国航空动力机械研究所 | Ventilation system for bearing cavities |
| CN108087121A (en) * | 2016-11-23 | 2018-05-29 | 中国航空动力机械研究所 | A kind of aero-engine eccentric contract |
-
2021
- 2021-05-14 CN CN202110526653.3A patent/CN113090392B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103982302A (en) * | 2014-05-23 | 2014-08-13 | 中国航空动力机械研究所 | Gas turbine generator set and cooling mechanism used for gas turbine generator set |
| CN104989531A (en) * | 2015-06-23 | 2015-10-21 | 中国航空动力机械研究所 | Ventilation system for bearing cavities |
| CN108087121A (en) * | 2016-11-23 | 2018-05-29 | 中国航空动力机械研究所 | A kind of aero-engine eccentric contract |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113530680A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Aviation turboshaft engine lubricating oil system and aviation turboshaft engine |
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| Publication number | Publication date |
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| CN113090392B (en) | 2022-01-07 |
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