CN112901351B - Bearing support structure of birotor gas turbine engine - Google Patents
Bearing support structure of birotor gas turbine engine Download PDFInfo
- Publication number
- CN112901351B CN112901351B CN201911218167.4A CN201911218167A CN112901351B CN 112901351 B CN112901351 B CN 112901351B CN 201911218167 A CN201911218167 A CN 201911218167A CN 112901351 B CN112901351 B CN 112901351B
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- Prior art keywords
- rotating shaft
- pressure oil
- bearing
- gas turbine
- support structure
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- 238000007789 sealing Methods 0.000 claims abstract description 7
- 230000009977 dual effect Effects 0.000 claims description 12
- 239000003921 oil Substances 0.000 description 72
- 230000000694 effects Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- 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
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Support Of The Bearing (AREA)
Abstract
The invention discloses a bearing support structure of a dual-rotor gas turbine engine, which comprises a first rotating shaft, a second rotating shaft and a bearing support, wherein the second rotating shaft is coaxially arranged in an inner cavity of the first rotating shaft, and the bearing support structure further comprises: the first bearing is formed between the first rotating shaft and the second rotating shaft, and the second bearing is sleeved outside the first rotating shaft; the first rotating shaft and the second rotating shaft are arranged on the bearing seat through the second bearing frame. The first bearing is composed of a first high-pressure oil cavity and a third high-pressure oil cavity which are formed between the first rotating shaft and the second rotating shaft, and the first high-pressure oil cavity and the third high-pressure oil cavity are sealed through dynamic sealing rings at two sides. The bearing support structure of the dual-rotor gas turbine engine can reduce the number of bearing frames of the existing engine and provide stable support for the engine; and its structure, novel in design, simple structure, stability is high, long service life, even good popularization and application value.
Description
Technical Field
The invention belongs to the technical field of gas turbine engines, and particularly relates to a bearing support structure of a double-rotor gas turbine engine.
Background
The gas generator of a dual rotor gas turbine engine, like a single rotor engine, also comprises a compressor, a combustion chamber and a turbine. In contrast, a dual rotor engine has two rotors. The compressor of the double-rotor engine is divided into a front part and a rear part, wherein the front part is called a low-pressure compressor, and the rear part is called a high-pressure compressor; the whole turbine is also divided into front and rear parts, the front part being called the high pressure turbine and the rear part being called the low pressure turbine. The low-pressure compressor is connected with the low-pressure turbine to form a low-pressure rotor; the high-pressure compressor is connected with the high-pressure turbine to form a high-pressure rotor. There is no mechanical connection between the two rotors, only pneumatic connection. The rotational speed of the two rotors may be different, in general the rotational speed of the high pressure rotor is higher than the rotational speed of the lower pressure rotor.
At present, most of the bearing systems of the double-rotor engine are arranged in a split mode, so that the force transmission path of the engine is longer, the length of the whole engine is longer, and the weight of the whole engine is obviously increased due to the fact that one more bearing frame is more obvious, and the control of the weight of the whole engine is not facilitated.
Disclosure of Invention
The invention solves the problems that: in view of the above-mentioned drawbacks of the prior art, a bearing support structure for a dual-rotor gas turbine engine is provided to reduce the number of bearing frames of the engine and provide stable support for the engine.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the invention provides a bearing support structure of a dual-rotor gas turbine engine, which comprises a first rotating shaft, a second rotating shaft and a bearing support, wherein the second rotating shaft is coaxially arranged in an inner cavity of the first rotating shaft, and the bearing support structure further comprises: the first bearing is formed between the first rotating shaft and the second rotating shaft, and the second bearing is sleeved outside the first rotating shaft; the first rotating shaft and the second rotating shaft are arranged on the bearing seat through the second bearing.
Further, in the bearing support structure of the dual-rotor gas turbine engine, the first bearing is composed of a first high-pressure oil cavity and a third high-pressure oil cavity formed between the first rotating shaft and the second rotating shaft, and the first high-pressure oil cavity and the third high-pressure oil cavity are sealed through dynamic sealing rings at two sides.
Further preferably, on the bearing supporting structure of the dual-rotor gas turbine engine, a second high-pressure oil cavity is formed in the inner side wall of the second rotating shaft at a position corresponding to the first high-pressure oil cavity, and the second high-pressure oil cavity is respectively communicated with the first high-pressure oil cavity and the third high-pressure oil cavity through a second oil inlet hole and a third oil inlet hole which are radially formed in the second rotating shaft.
Further preferably, on the bearing support structure of the dual-rotor gas turbine engine, the second oil inlet hole is located in the middle of the second high-pressure oil cavity, and the third oil inlet hole is located at one end of the second high-pressure oil cavity.
Further preferably, in the dual rotor gas turbine engine bearing support structure, the second high pressure oil chamber is sealed by an inner bushing disposed on an inner sidewall of the second shaft.
Further, in the bearing support structure of the dual-rotor gas turbine engine, the third high-pressure oil cavity is communicated with the balls in the second bearing through a fourth oil inlet hole radially formed in the first rotating shaft.
Further, on the bearing supporting structure of the dual-rotor gas turbine engine, a first oil inlet hole communicated with the first high-pressure oil cavity is radially formed in the first rotating shaft, and the first oil inlet hole is communicated with the high-pressure oil supply pipeline through an oil supply sealing ring sleeved on the first rotating shaft.
Further preferably, on the bearing support structure of the dual-rotor gas turbine engine, at least two first oil inlet holes are arranged in a staggered mode.
Further, on the dual rotor gas turbine engine bearing support structure, the first shaft is a gas generator shaft.
Further, on the bearing support structure of the dual-rotor gas turbine engine, the second rotating shaft is a power output shaft or a low-pressure rotor shaft.
Compared with the prior art, the invention has the following technical effects:
according to the bearing support structure of the dual-rotor gas turbine engine, the first bearing and the second bearing are respectively arranged on the inner side and the outer side of the first rotating shaft, when the first rotating shaft and the second rotating shaft rotate at high speed, an oil film formed by high-pressure oil in the first high-pressure oil cavity and the second high-pressure oil cavity forms a sliding first bearing so as to support the first rotating shaft, and finally the first rotating shaft and the second rotating shaft are erected on the bearing seat through the second bearing, so that the number of bearing frames of the existing engine is reduced, stable support is provided for the engine, and obvious advantage effects are brought to the total length and the weight of the engine; the bearing supporting structure of the dual-rotor gas turbine engine is novel in design, simple in structure, high in stability, long in service life, uniform and good in popularization and application value.
Drawings
FIG. 1 is a schematic cross-sectional structural view of a dual rotor gas turbine engine bearing support structure of the present invention;
FIG. 2 is a schematic view of a partial structure of a dual rotor gas turbine engine bearing support structure of the present invention;
wherein, each reference sign is:
1-first rotating shaft, 2-second rotating shaft, 3-first bearing, 4-second bearing, 5-bearing seat, 6-first high-pressure oil cavity, 7-second oil inlet hole, 8-second high-pressure oil cavity, 9-third oil inlet hole, 10-third high-pressure oil cavity and 11-fourth oil inlet hole. 12-moving sealing rings, 13-inner bushings, 14-first oil inlets, 15-oil supply sealing rings and 16-high-pressure oil supply pipelines.
Detailed Description
The present invention will be described in detail and in detail by way of the following examples, which are not intended to limit the scope of the invention, for better understanding of the invention.
Example 1
Referring to fig. 1, the present embodiment provides a bearing support structure of a dual-rotor gas turbine engine, including a first rotating shaft 1 and a second rotating shaft 2 coaxially disposed in an inner cavity of the first rotating shaft 1, and further including: a first bearing 3 formed between the first rotating shaft 1 and the second rotating shaft 2, and a second bearing 4 sleeved outside the first rotating shaft 1; the first rotating shaft 1 and the second rotating shaft 2 are erected on a bearing seat 5 through the second bearing 4.
In this embodiment, the first rotating shaft 1 is a gas generator shaft. The second rotating shaft 2 is a power output shaft or a low-voltage rotor shaft. The second rotating shaft 2 is sleeved in the inner cavity of the first rotating shaft 1, and the double-rotor gas turbine engine generates relative rotation during operation.
In this embodiment, the first bearing 3 and the second bearing 4 are ball bearings, and are oil-supplying under the ring, so as to provide lubricating oil for the first bearing 3 and the second bearing 4, and reduce friction force generated by relative rotation between the first rotating shaft 1 and the second rotating shaft 2.
Example 2
With continued reference to fig. 1, the bearing support structure for a dual-rotor gas turbine engine provided in this embodiment is the same as that of the above embodiment 1, and includes a first rotating shaft 1 and a second rotating shaft 2 coaxially disposed in an inner cavity of the first rotating shaft 1, and further includes: a first bearing 3 formed between the first rotating shaft 1 and the second rotating shaft 2, and a second bearing 4 sleeved outside the first rotating shaft 1; the first rotating shaft 1 and the second rotating shaft 2 are erected on a bearing seat 5 through the second bearing 4.
Unlike the above embodiment 1, as shown in fig. 1-2, the first bearing 3 is composed of a first high-pressure oil chamber 6 and a third high-pressure oil chamber 10 formed between the first rotating shaft 1 and the second rotating shaft 2, and the first high-pressure oil chamber 6 and the third high-pressure oil chamber 10 are sealed by a movable seal ring 12 between them and on both sides. By arranging the first bearing 3 and the second bearing 4 on the inner side and the outer side of the first rotating shaft 1 respectively, when the first rotating shaft 1 and the second rotating shaft 2 rotate at high speed, an oil film formed by high-pressure oil in the first high-pressure oil cavity 6 and the second high-pressure oil cavity 8 forms a sliding first bearing 3 so as to support the first rotating shaft 1; and finally, the first rotating shaft 3 and the second rotating shaft 4 are erected on a bearing seat 5 through the second bearing 4, so that the number of the existing engine bearing frames is reduced, and stable support is provided for the engine.
In this embodiment, as shown in fig. 1-2, a second high-pressure oil chamber 8 is provided on the inner side wall of the second rotating shaft 2 corresponding to the first high-pressure oil chamber 6, and the second high-pressure oil chamber 8 is respectively communicated with the first high-pressure oil chamber 6 and the third high-pressure oil chamber 10 through a second oil inlet hole 7 and a third oil inlet hole 9 radially provided on the second rotating shaft 2. And the second oil inlet hole 7 is positioned in the middle of the second high-pressure oil cavity 8, and the third oil inlet hole 9 is positioned at one end of the second high-pressure oil cavity 8.
In this embodiment, as shown in fig. 1-2, the second high-pressure oil chamber 8 is sealed by an inner bushing 13 disposed on the inner side wall of the second rotating shaft 2, and the inner bushing 13 is in an annular structure, and is disposed on the inner side wall of the second rotating shaft 2 by welding to seal the second high-pressure oil chamber 8.
In this embodiment, as shown in fig. 1-2, the third high-pressure oil chamber 10 is communicated with the balls in the second bearing 4 through a fourth oil inlet hole 11 radially formed in the first rotating shaft 1, so as to perform oil supply under the ring for the second bearing 4.
With continued reference to fig. 1, the first rotating shaft 1 is radially provided with a first oil inlet hole 14 that is communicated with the first high-pressure oil cavity 6, and the first oil inlet hole 14 is communicated with a high-pressure oil supply pipeline 16 through an oil supply sealing ring 15 that is sleeved on the first rotating shaft 1. And at least two first oil inlets 14 are staggered.
In this embodiment, the first rotating shaft 1 is a gas generator shaft. The second rotating shaft 2 is a power output shaft or a low-voltage rotor shaft. The second rotating shaft 2 is sleeved in the inner cavity of the first rotating shaft 1, and the first bearing 3 formed by a high-pressure oil film between the second rotating shaft and the inner cavity generates relative rotation when the double-rotor gas turbine engine runs.
According to the bearing support structure of the dual-rotor gas turbine engine, the first bearing 3 and the second bearing 4 are respectively arranged on the inner side and the outer side of the first rotating shaft 1, when the first rotating shaft 1 and the second rotating shaft 2 rotate at a high speed, an oil film formed by high-pressure oil in the first high-pressure oil cavity 6 and the second high-pressure oil cavity 8 forms a sliding first bearing 3 so as to support the first rotating shaft 1, and finally the first rotating shaft 1 and the second rotating shaft 2 are erected on the bearing seat 5 through the second bearing 4, so that the number of bearing frames of the existing engine is reduced, stable support is provided for the engine, and obvious advantage effects are brought to the total length and the weight of the engine; the bearing supporting structure of the dual-rotor gas turbine engine is novel in design, simple in structure, high in stability, long in service life, uniform and good in popularization and application value.
The above description of the specific embodiments of the present invention has been given by way of example only, and the present invention is not limited to the above described specific embodiments. Any equivalent modifications and substitutions for the present invention will occur to those skilled in the art, and are also within the scope of the present invention. Accordingly, equivalent changes and modifications are intended to be included within the scope of the present invention without departing from the spirit and scope thereof.
Claims (8)
1. The utility model provides a birotor gas turbine engine bearing support structure, includes first pivot (1) and coaxial set up in second pivot (2) of first pivot (1) inner chamber, its characterized in that still includes: a first bearing (3) formed between the first rotating shaft (1) and the second rotating shaft (2), and a second bearing (4) sleeved outside the first rotating shaft (1); the first rotating shaft (1) and the second rotating shaft (2) are erected on a bearing seat (5) through the second bearing (4);
the first bearing (3) is composed of a first high-pressure oil cavity (6) and a third high-pressure oil cavity (10) which are formed between the first rotating shaft (1) and the second rotating shaft (2), and the space between the first high-pressure oil cavity (6) and the third high-pressure oil cavity (10) and the two sides of the space are sealed by movable sealing rings (12);
the first rotating shaft (1) is a gas generator shaft.
2. The bearing support structure of a dual-rotor gas turbine engine according to claim 1, wherein a second high-pressure oil cavity (8) is formed in the inner side wall of the second rotating shaft (2) at a position corresponding to the first high-pressure oil cavity (6), and the second high-pressure oil cavity (8) is respectively communicated with the first high-pressure oil cavity (6) and the third high-pressure oil cavity (10) through a second oil inlet hole (7) and a third oil inlet hole (9) which are radially formed in the second rotating shaft (2).
3. The dual rotor gas turbine engine bearing support structure of claim 2, wherein the second oil inlet hole (7) is located in the middle of the second high pressure oil chamber (8), and the third oil inlet hole (9) is located at one end of the second high pressure oil chamber (8).
4. The dual rotor gas turbine engine bearing support structure of claim 2, wherein the second high pressure oil chamber (8) is sealed by an inner bushing (13) provided on an inner sidewall of the second rotating shaft (2).
5. The dual rotor gas turbine engine bearing support structure of claim 1, characterized in that the third high pressure oil chamber (10) communicates with balls in the second bearing (4) through a fourth oil inlet hole (11) radially open on the first shaft (1).
6. The bearing support structure of a dual rotor gas turbine engine according to claim 1, characterized in that a first oil inlet hole (14) communicated with the first high pressure oil cavity (6) is radially formed on the first rotating shaft (1), and the first oil inlet hole (14) is communicated with a high pressure oil supply pipeline (16) through an oil supply seal ring (15) sleeved on the first rotating shaft (1).
7. The dual rotor gas turbine engine bearing support structure of claim 6, wherein at least two of the first oil inlet holes (14) are staggered.
8. The dual rotor gas turbine engine bearing support structure of claim 1, characterized in that the second rotating shaft (2) is a power take-off shaft or a low pressure rotor shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911218167.4A CN112901351B (en) | 2019-12-03 | 2019-12-03 | Bearing support structure of birotor gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911218167.4A CN112901351B (en) | 2019-12-03 | 2019-12-03 | Bearing support structure of birotor gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112901351A CN112901351A (en) | 2021-06-04 |
| CN112901351B true CN112901351B (en) | 2023-11-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911218167.4A Active CN112901351B (en) | 2019-12-03 | 2019-12-03 | Bearing support structure of birotor gas turbine engine |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105683528A (en) * | 2013-10-10 | 2016-06-15 | 斯奈克玛 | Device for transferring oil between two repositories rotating relative to each other, and propeller turbomachine for an aircraft with such a device |
| CN105899763A (en) * | 2014-01-23 | 2016-08-24 | 斯奈克玛 | Turbomachine bearing housing |
| CN106460554A (en) * | 2014-04-29 | 2017-02-22 | 赛峰飞机发动机公司 | Assembly for aircraft turbine engine and method for mounting same |
| CN107060992A (en) * | 2017-05-04 | 2017-08-18 | 中国北方发动机研究所(天津) | One kind is combined concentrically birotor exhaust turbocharging system structure |
| RU185233U1 (en) * | 2018-07-25 | 2018-11-27 | Юрий Борисович Назаренко | GAS-TURBINE ENGINE ROTOR SUPPORT |
| CN211202129U (en) * | 2019-12-03 | 2020-08-07 | 上海尚实能源科技有限公司 | Bearing supporting structure of double-rotor gas turbine engine |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014098962A1 (en) * | 2012-12-17 | 2014-06-26 | United Technologies Corporation | Two spool gas generator to create family of gas turbine engines |
-
2019
- 2019-12-03 CN CN201911218167.4A patent/CN112901351B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105683528A (en) * | 2013-10-10 | 2016-06-15 | 斯奈克玛 | Device for transferring oil between two repositories rotating relative to each other, and propeller turbomachine for an aircraft with such a device |
| CN105899763A (en) * | 2014-01-23 | 2016-08-24 | 斯奈克玛 | Turbomachine bearing housing |
| CN106460554A (en) * | 2014-04-29 | 2017-02-22 | 赛峰飞机发动机公司 | Assembly for aircraft turbine engine and method for mounting same |
| CN107060992A (en) * | 2017-05-04 | 2017-08-18 | 中国北方发动机研究所(天津) | One kind is combined concentrically birotor exhaust turbocharging system structure |
| RU185233U1 (en) * | 2018-07-25 | 2018-11-27 | Юрий Борисович Назаренко | GAS-TURBINE ENGINE ROTOR SUPPORT |
| CN211202129U (en) * | 2019-12-03 | 2020-08-07 | 上海尚实能源科技有限公司 | Bearing supporting structure of double-rotor gas turbine engine |
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| Publication number | Publication date |
|---|---|
| CN112901351A (en) | 2021-06-04 |
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