CN116044569A - Low-vibration coupling high-low pressure turbine layout structure of aeroengine - Google Patents
Low-vibration coupling high-low pressure turbine layout structure of aeroengine Download PDFInfo
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- CN116044569A CN116044569A CN202310318033.XA CN202310318033A CN116044569A CN 116044569 A CN116044569 A CN 116044569A CN 202310318033 A CN202310318033 A CN 202310318033A CN 116044569 A CN116044569 A CN 116044569A
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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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/02—Plural gas-turbine plants having a common power output
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
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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
Abstract
The invention belongs to the field of overall structure layout design of aeroengines, and discloses a low-vibration coupling aeroengine high-low pressure turbine layout structure which comprises a high-pressure turbine, a low-pressure turbine and a turbine inter-stage bearing frame which are coaxially arranged, wherein a high-pressure turbine rear journal of the high-pressure turbine is rotatably connected with a low-pressure turbine journal of the low-pressure turbine through an intermediate fulcrum, the turbine inter-stage bearing frame is rotatably connected with the high-pressure turbine rear journal or the low-pressure turbine journal through a rear fulcrum, the intermediate fulcrum, the rear fulcrum and the turbine inter-stage bearing frame are radially arranged in a same ring, and the turbine inter-stage bearing frame is positioned between the high-pressure turbine and the low-pressure turbine.
Description
Technical Field
The invention belongs to the field of overall structural layout design of aeroengines, and particularly relates to a low-vibration coupling high-low pressure turbine layout structure of an aeroengine.
Background
The modern aero-engine is mainly a gas turbine, the aero-engine is light and heavy-duty equipment, so that the structural quality is reduced, the structural efficiency of the whole machine is improved, the modern aero-engine is mainly provided with a layout structure of a middle supporting point, a turbine rear bearing frame and a turbine inter-stage bearing frame at a turbine end, and the two layout structures use a single bearing frame at the turbine end, so that the vibration coupling problem of a structural system is solved while the quality of a stator structure is controlled.
In the layout structure of the middle pivot and the turbine rear bearing frame, the middle pivot is connected with the turbine ends of the high-pressure and low-pressure rotors, the rotor motion is mutually influenced, the load is directly transmitted, the rear pivot is arranged behind the low-pressure turbine, the axial direction is far away from the middle pivot, the bearing capacity is lower, the low-pressure turbine is contained in the transmission route of the middle pivot and the turbine rear bearing frame, the vibration coupling of the double-rotor system is further enhanced, as shown in fig. 2, in the layout structure of the turbine inter-stage bearing frame, the bearing frame is positioned between the high-pressure turbine and the low-pressure turbine, the rear pivot of the high-pressure rotor and the rear pivot of the low-pressure rotor are supported, and the rotors are easy to generate interactive excitation through the motion and deformation of the bearing seat, so that the double-rotor bearing structure system generates vibration coupling.
Therefore, it is necessary to design a low vibration coupling high-low pressure turbine layout structure of an aeroengine, and meanwhile, an intermediate fulcrum and a turbine interstage bearing frame are adopted, and the intermediate fulcrum, a rear fulcrum and the turbine interstage bearing frame are radially arranged in the same ring, so that the load outward transmission route of the turbine end rotor is optimized, the vibration coupling between the double rotors at the turbine end and the bearing structure is reduced, the bearing capacity of the rear fulcrum is improved, and meanwhile, the bearing structure is closer to the mass center of the turbine part, and the transverse deformation control and the pneumatic efficiency maintenance of the turbine rotor are facilitated.
Disclosure of Invention
In order to solve the technical problems, the invention provides a low-vibration coupling high-low pressure turbine layout structure of an aeroengine, which aims to solve the problems of long turbine end force transmission route, low rear supporting point bearing capacity and prominent vibration coupling of a double-rotor and bearing structure in the prior art, and the invention adopts the following technical scheme:
the low-vibration coupling aeroengine high-low pressure turbine layout structure comprises a high-pressure turbine, a low-pressure turbine and a turbine inter-stage bearing frame which are coaxially arranged, wherein a high-pressure turbine rear journal of the high-pressure turbine is rotatably connected with a low-pressure turbine journal of the low-pressure turbine through an intermediate fulcrum, and the turbine inter-stage bearing frame is rotatably connected with the high-pressure turbine rear journal or the low-pressure turbine journal through a rear fulcrum;
the intermediate fulcrum, the rear fulcrum and the turbine inter-stage bearing frame are arranged in a radial same ring, and the turbine inter-stage bearing frame is positioned between the high-pressure turbine and the low-pressure turbine in the axial direction.
Further, when the turbine stage bearing frame and the low pressure turbine shaft neck are rotatably connected through the rear supporting point, the high pressure turbine rear shaft neck, the intermediate supporting point, the low pressure turbine shaft neck, the rear supporting point and the turbine stage bearing frame are distributed in sequence in the direction from inside to outside.
Further, the outer ring of the intermediate fulcrum is arranged on the radial inner side of the low-pressure turbine journal, and the inner ring of the intermediate fulcrum is arranged on the radial outer side of the high-pressure turbine rear journal; the inner ring of the rear pivot is arranged on the radial outer side of the low-pressure turbine journal, and the outer ring of the rear pivot is arranged on the radial inner side of the turbine interstage bearing frame.
Further, the low pressure turbine journal is one or two;
when one, the low pressure turbine journal is connected to the low pressure turbine shaft and the low pressure turbine journal is disposed toward the high pressure turbine, the axial and torque loads of the low pressure turbine being transferred through the low pressure turbine journal and the low pressure turbine shaft.
Further, when the number of the low-pressure turbine journals is two, the two low-pressure turbine journals are respectively a low-pressure turbine front journal and a low-pressure turbine rear journal, the low-pressure turbine front journal is arranged on one side of the low-pressure turbine facing the high-pressure turbine, the low-pressure turbine rear journal is arranged on one side of the low-pressure turbine facing away from the high-pressure turbine, the low-pressure turbine front journal is connected with an intermediate fulcrum and a rear fulcrum, and the low-pressure turbine rear journal is connected with a low-pressure turbine shaft;
the axial and torque loads of the low pressure turbine are transferred through the low pressure turbine aft journal and the low pressure turbine shaft.
Further, radial load of the high-pressure turbine is transmitted to the turbine inter-stage bearing frame through the high-pressure turbine rear journal, the intermediate fulcrum, the low-pressure turbine journal and the rear fulcrum in sequence;
radial loads of the low-pressure turbine are transmitted to the turbine inter-stage bearing frame through the low-pressure turbine journal and the rear fulcrum.
Further, when the turbine inter-stage bearing frame and the high-pressure turbine rear journal are rotatably connected through the rear pivot, the low-pressure turbine shaft, the intermediate pivot, the high-pressure turbine rear journal, the rear pivot and the turbine inter-stage bearing frame are sequentially distributed in the direction from inside to outside.
Further, the low-pressure turbine journal is connected to the low-pressure turbine shaft, the inner ring of the intermediate fulcrum is mounted on the low-pressure turbine shaft, and the outer ring is mounted on the radial inner side of the high-pressure turbine rear journal; the inner ring of the rear pivot is arranged on the radial outer side of the rear journal of the high-pressure turbine, and the outer ring of the rear pivot is arranged on the radial inner side of the inter-stage bearing frame of the turbine.
Further, radial load of the high-pressure turbine is transmitted to the turbine inter-stage bearing frame through the high-pressure turbine rear journal and the rear fulcrum, and radial load of the low-pressure turbine is transmitted to the turbine inter-stage bearing frame through the low-pressure turbine journal, the middle fulcrum, the high-pressure turbine rear journal and the rear fulcrum.
Further, the turbine interstage bearing frame comprises a bearing seat, a bearing cone shell and a bearing radials, wherein the radial inner side of the bearing seat is connected with the outer ring of the rear supporting point, and the radial outer side of the bearing seat is fixedly connected with a plurality of the bearing radials through the bearing cone shell.
The invention has the following beneficial effects:
1. according to the invention, the intermediate fulcrum, the rear fulcrum and the turbine-stage bearing frame are arranged in the same radial ring, so that the load transmission route of the turbine-end rotor is optimized, and the vibration coupling of the turbine-end structure is reduced;
2. according to the invention, the bearing frame is arranged between the high-pressure turbine and the low-pressure turbine in the axial direction and is closer to the mass center of the turbine part, so that the transverse deformation control and the pneumatic efficiency maintenance of the turbine rotor are facilitated;
3. according to the invention, the rear supporting point is arranged on the radial outer side of the intermediate supporting point, so that the diameter of the rear supporting point is larger, more rollers can be accommodated, and the bearing capacity of the rear supporting point is improved.
Drawings
FIG. 1 is a schematic diagram of a layout structure of a conventional turbine end 'intermediate fulcrum + turbine rear load frame';
FIG. 2 is a schematic diagram of a conventional turbine end "turbine inter-stage load frame" layout structure;
FIG. 3 is a schematic layout of embodiment 1 of the present invention;
FIG. 4 is a schematic diagram of the layout structure of embodiment 2 of the present invention;
FIG. 5 is a schematic diagram showing the layout structure of embodiment 3 of the present invention;
in the figure: A. intermediate supporting point B, turbine inter-stage bearing frame, 1, high-pressure turbine, 2, high-pressure turbine rear journal, 3, high-pressure turbine shaft, 4, low-pressure turbine, 5, low-pressure turbine journal, 6, low-pressure turbine shaft, 7, rear supporting point, 8, turbine rear bearing frame, B1, bearing pedestal, B2, bearing cone shell, B3 and bearing radials.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to fig. 1 to 5 in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, but not all embodiments, and the technical means used in the embodiments are conventional means known to those skilled in the art unless specifically indicated.
Aiming at the defects or improvement demands of the prior art, the invention provides a low-vibration coupling high-low pressure turbine layout structure of an aeroengine, which optimizes the load transmission route of a turbine end rotor, reduces vibration coupling between double rotors at the turbine end and between the double rotors and a bearing frame and improves the bearing capacity of a rear fulcrum by arranging an intermediate fulcrum, the rear fulcrum and the bearing frame between the turbine stages in the radial same ring.
1-5, a schematic cross section is shown below the center line of rotation, and it can be understood that the present invention is a three-dimensional structure axisymmetric along the center line of rotation, and the cross section is used for illustration in the drawings for convenience of illustration; in addition, unless specifically stated otherwise, the following references to the directional terms "front" and "rear" refer to the left in the drawings, and the directional terms "rear" and "right in the drawings.
Referring to fig. 3-5, a low vibration coupling aeroengine high-low pressure turbine layout structure comprises a high-pressure turbine 1, a low-pressure turbine 4 and a turbine inter-stage bearing frame B which are coaxially arranged, wherein a high-pressure turbine rear journal 2 of the high-pressure turbine 1 is rotatably connected with a low-pressure turbine journal 5 of the low-pressure turbine 4 through an intermediate fulcrum A, and the turbine inter-stage bearing frame B is rotatably connected with the high-pressure turbine rear journal 2 or the low-pressure turbine journal 5 through a rear fulcrum 7;
the intermediate fulcrum A, the rear fulcrum 7 and the turbine stage bearing frame B are arranged in a radial same ring, and the turbine stage bearing frame B is positioned between the high-pressure turbine 1 and the low-pressure turbine 4 in the axial direction.
The journals of the high-pressure turbine 1, the low-pressure turbine 4 are oppositely arranged and positioned between the two, the intermediate fulcrum a and the rear fulcrum 7 are bearing assemblies, such as one or a combination of rolling rod bearings, ball bearings and sliding bearings, the intermediate fulcrum a is a rotary connection part between the axial directions of the high-pressure turbine and the low-pressure turbine, the rear fulcrum 7 is a rotary connection part between the turbine inter-stage bearing frame B and the high-pressure turbine 1 or the low-pressure turbine 4, the rear fulcrum 7 is connected with the low-pressure turbine journal 5 when the high-pressure turbine rear journal 2 is positioned on the radial inner side of the low-pressure turbine journal 5, the rear fulcrum 7 is connected with the high-pressure turbine rear journal 2 when the high-pressure turbine rear journal 2 is positioned on the radial outer side of the low-pressure turbine journal 5, and the intermediate fulcrum a, the rear fulcrum 7 and the turbine inter-stage bearing frame B are all arranged in the same ring regardless of the arrangement, and it is understood that the same ring arrangement means that the components are positioned on the same radial straight line.
Referring to fig. 1 and 3, the force transmission route of the radial load between the intermediate fulcrum a and the rear fulcrum 7 is effectively shortened, the load in fig. 1 is transmitted from the intermediate fulcrum a to the rear fulcrum 7, and the load needs to pass through the low-pressure turbine journal 5 and the low-pressure turbine shaft 6, namely the rear fulcrum 7 is indirectly restrained to the intermediate fulcrum a;
in fig. 3, the load is transferred from the intermediate fulcrum a to the rear fulcrum 7, and only the bearing inner and outer rings mounted on the low-pressure turbine journal 5 are needed to pass through, namely, the rear fulcrum 7 is directly restrained to the intermediate fulcrum a;
meanwhile, in the figure 1, the load generated by the low-pressure turbine 4 is partially transmitted to the high-pressure turbine 1 along the axial direction, and in the figure 3, the load at the turbine end is completely transmitted to the rear supporting point 7 along the radial direction, so that the mutual excitation between the double rotors is reduced, and the vibration coupling of the double rotors is effectively improved.
Compared with the prior art, the invention can optimize the force transmission route by arranging the intermediate fulcrum A, the rear fulcrum 7 and the turbine inter-stage bearing frame B in the same radial ring, further reduce the vibration coupling between the turbine-end double rotors and the bearing frame, and improve the bearing capacity of the rear fulcrum 7 by arranging the rear fulcrum 7 on the radial outer side of the intermediate fulcrum A, wherein the diameter of the rear fulcrum 7 is larger, and more rollers can be accommodated.
In addition, in the invention, the turbine interstage bearing frame B is positioned between the high-pressure turbine 1 and the low-pressure turbine 4 in the axial direction and is arranged near the mass center of the turbine part, so that the turbine deformation control capability is enhanced, the turbine blade tip clearance and the aerodynamic efficiency are maintained, and the rear supporting point bearing capability is improved.
With the intermediate fulcrum a, the rear fulcrum 7 and the turbine stage bearing frame B being disposed radially in common, the present invention includes, but is not limited to, the following three specific arrangements, which are specifically described below:
referring to fig. 3, example 1: when the turbine inter-stage bearing frame B and the low-pressure turbine journal 5 are rotatably connected through the rear supporting point 7, the high-pressure turbine rear journal 2, the intermediate supporting point A, the low-pressure turbine journal 5, the rear supporting point 7 and the turbine inter-stage bearing frame B are distributed in sequence in the radial direction from inside to outside.
That is, example 1 is an embodiment in which the low pressure turbine journal 5 is radially outward of the high pressure turbine aft journal 2.
Further, the outer ring of the intermediate fulcrum a is mounted radially inside the low pressure turbine journal 5, and the inner ring thereof is mounted radially outside the high pressure turbine aft journal 2; the inner ring of said rear fulcrum 7 is mounted radially outside the low-pressure turbine journal 5 and the outer ring thereof is mounted radially inside the turbine inter-stage bearing frame B.
Further, the low pressure turbine journal 5 is one or two.
When two low-pressure turbine journals 5 are provided, a layout structure of example 2 is formed, and it should be noted that, in example 2, the embodiment is extended from the embodiment 1, and both embodiments of the low-pressure turbine journals 5 radially outside the high-pressure turbine rear journal 2 are adopted, and the structural difference is that the number and distribution positions of the low-pressure turbine journals 5 are different:
referring to fig. 4, example 2: when the number of the low-pressure turbine journals 5 is two, the two low-pressure turbine journals are respectively a low-pressure turbine front journal and a low-pressure turbine rear journal, the low-pressure turbine front journal is arranged on one side of the low-pressure turbine 4 facing the high-pressure turbine 1, the low-pressure turbine rear journal is arranged on one side of the low-pressure turbine 4 facing away from the high-pressure turbine 1, the low-pressure turbine front journal is connected with an intermediate fulcrum A and a rear fulcrum 7, and the low-pressure turbine rear journal is connected with a low-pressure turbine shaft 6;
the axial and torque loads of the low pressure turbine 4 are transferred through the low pressure turbine aft journal and low pressure turbine shaft 6.
The embodiment 1 and the embodiment 2 of the present invention generate different load transmission routes by different numbers and distribution positions of the low-pressure turbine journals 5, and the difference is that: in example 1, the low pressure turbine 4 is transmitted from the disk front side via the low pressure turbine journal 5 in all of its lateral, axial and torque loads; in example 2, the transverse load of the low pressure turbine 4 is transferred from the forward side of the disk via the low pressure turbine forward journal and the axial and torque loads are transferred from the aft side of the disk via the low pressure turbine aft journal.
Compared with example 1, the load of example 2 is transmitted along the front and rear of the wheel disc separately, the stress level of the journal is reduced, and simultaneously, the front and rear journals generate higher angular constraint, which is beneficial to controlling the local angular deformation of the low-pressure turbine 4, but the structural processing and assembly difficulties are higher.
Referring to fig. 5, example 3: when the turbine inter-stage bearing frame B and the high-pressure turbine rear journal 2 are rotatably connected through the rear supporting point 7, the low-pressure turbine shaft 6, the intermediate supporting point A, the high-pressure turbine rear journal 2, the rear supporting point 7 and the turbine inter-stage bearing frame B are distributed in sequence in the radial direction from inside to outside.
Example 3 is an embodiment in which the high pressure turbine aft journal 2 is located radially outward of the low pressure turbine journal 5.
Further, the low pressure turbine 4 is cantilever-connected to the low pressure turbine shaft 6 through the low pressure turbine journal 5, the inner ring of the intermediate fulcrum a is mounted on the low pressure turbine shaft 6, and the outer ring thereof is mounted radially inside the high pressure turbine rear journal 2; the inner ring of the rear pivot 7 is mounted radially outside the high-pressure turbine rear journal 2 and the outer ring thereof is mounted radially inside the turbine-stage bearing frame B.
Compared with the embodiments 1 and 2, in the embodiment 3, the transverse load between the turbine rotors is opposite to the radial transmission sequence, the transverse load of the low-pressure turbine 4 is converged with the high-pressure turbine 1 and then transmitted to the turbine inter-stage bearing frame B, so that the rigidity of the rear journal 2 of the high-pressure turbine is improved while the excitation of the low-pressure turbine 4 by the high-pressure turbine 1 is reduced, and the rotating speed and the strength level of the rear supporting point 7 are further improved.
In the above three embodiments, the low-pressure turbine shaft 6 at the lower side in the drawing is the structure closest to the shaft center, and the high-pressure turbine shaft 3 is disposed at the side of the high-pressure turbine 1 facing away from the low-pressure turbine 4.
In addition, the turbine interstage bearing frame B comprises a bearing seat B1, a bearing cone shell B2 and a bearing radials B3, wherein the radial inner side of the bearing seat B1 is connected with an outer ring of the rear supporting point 7, and the radial outer side of the bearing seat B1 is fixedly connected with a plurality of the bearing radials B3 through the bearing cone shell B2.
The above embodiments are only illustrative of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention, and various modifications, variations, alterations, substitutions made by those skilled in the art to the technical solution of the present invention should fall within the protection scope defined by the claims of the present invention without departing from the spirit of the design of the present invention.
Claims (10)
1. The utility model provides a low vibration coupling's aeroengine high-low pressure turbine overall arrangement structure, includes high-pressure turbine (1), low-pressure turbine (4) and turbine inter-stage bearing frame (B) of coaxial setting, its characterized in that: the high-pressure turbine rear journal (2) of the high-pressure turbine (1) is rotatably connected with the low-pressure turbine journal (5) of the low-pressure turbine (4) through an intermediate fulcrum (A), and the turbine inter-stage bearing frame (B) is rotatably connected with the high-pressure turbine rear journal (2) or the low-pressure turbine journal (5) through a rear fulcrum (7);
the intermediate fulcrum (A), the rear fulcrum (7) and the turbine inter-stage bearing frame (B) are arranged in a radial same ring, and the turbine inter-stage bearing frame (B) is positioned between the high-pressure turbine (1) and the low-pressure turbine (4) in the axial direction.
2. A low vibration coupled aeroengine high and low pressure turbine layout structure as claimed in claim 1, wherein: when the turbine inter-stage bearing frame (B) and the low-pressure turbine shaft neck (5) are rotatably connected through the rear supporting point (7), the high-pressure turbine rear shaft neck (2), the intermediate supporting point (A), the low-pressure turbine shaft neck (5), the rear supporting point (7) and the turbine inter-stage bearing frame (B) are distributed in sequence in the radial direction from inside to outside.
3. A low vibration coupled aeroengine high and low pressure turbine layout structure as claimed in claim 2, wherein: the outer ring of the intermediate fulcrum (A) is arranged on the radial inner side of the low-pressure turbine journal (5), and the inner ring of the intermediate fulcrum (A) is arranged on the radial outer side of the high-pressure turbine rear journal (2); the inner ring of the rear fulcrum (7) is arranged on the radial outer side of the low-pressure turbine journal (5), and the outer ring of the rear fulcrum is arranged on the radial inner side of the turbine stage bearing frame (B).
4. A low vibration coupled aeroengine high and low pressure turbine layout structure as claimed in claim 2, wherein: -one or two low-pressure turbine journals (5);
when one, the low pressure turbine journal (5) is connected to a low pressure turbine shaft (6), and the low pressure turbine journal (5) is disposed toward the high pressure turbine (1), and axial and torque loads of the low pressure turbine (4) are transmitted through the low pressure turbine journal (5) and the low pressure turbine shaft (6).
5. The low vibration coupled high and low pressure turbine layout structure of an aircraft engine of claim 4, wherein: when the number of the low-pressure turbine journals (5) is two, the low-pressure turbine journals are respectively a low-pressure turbine front journal and a low-pressure turbine rear journal, the low-pressure turbine front journal is arranged on one side of the low-pressure turbine (4) facing the high-pressure turbine (1), and the low-pressure turbine rear journal is arranged on one side of the low-pressure turbine (4) facing away from the high-pressure turbine (1);
the low-pressure turbine front journal is connected with an intermediate fulcrum (A) and a rear fulcrum (7), and the low-pressure turbine rear journal is connected with a low-pressure turbine shaft (6);
the axial and torque loads of the low pressure turbine (4) are transferred through the low pressure turbine aft journal and the low pressure turbine shaft (6).
6. A low vibration coupled aeroengine high and low pressure turbine layout structure according to any of claims 2-5, wherein: radial load of the high-pressure turbine (1) is transmitted to the turbine inter-stage bearing frame (B) through the high-pressure turbine rear journal (2), the intermediate fulcrum (A), the low-pressure turbine journal (5) and the rear fulcrum (7) in sequence;
the radial load of the low-pressure turbine (4) is transmitted to the turbine inter-stage bearing frame (B) through the low-pressure turbine journal (5) and the rear fulcrum (7).
7. A low vibration coupled aeroengine high and low pressure turbine layout structure as claimed in claim 1, wherein: when the turbine inter-stage bearing frame (B) and the high-pressure turbine rear shaft neck (2) are rotatably connected through the rear supporting point (7), the low-pressure turbine shaft (6), the intermediate supporting point (A), the high-pressure turbine rear shaft neck (2), the rear supporting point (7) and the turbine inter-stage bearing frame (B) are sequentially distributed in the radial direction from inside to outside.
8. The low vibration coupled high and low pressure turbine layout structure of an aircraft engine of claim 7, wherein: the low-pressure turbine journal (5) is connected to the low-pressure turbine shaft (6), the inner ring of the intermediate fulcrum (A) is arranged on the low-pressure turbine shaft (6), and the outer ring of the intermediate fulcrum (A) is arranged on the radial inner side of the high-pressure turbine rear journal (2); the inner ring of the rear supporting point (7) is arranged on the radial outer side of the rear journal (2) of the high-pressure turbine, and the outer ring of the rear supporting point is arranged on the radial inner side of the inter-turbine stage bearing frame (B).
9. The low vibration coupled high and low pressure turbine layout structure of an aircraft engine of claim 7, wherein: radial load of the high-pressure turbine (1) is transmitted to the turbine inter-stage bearing frame (B) through the high-pressure turbine rear journal (2) and the rear supporting point (7), and radial load of the low-pressure turbine (4) is transmitted to the turbine inter-stage bearing frame (B) through the low-pressure turbine journal (5), the intermediate supporting point (A), the high-pressure turbine rear journal (2) and the rear supporting point (7).
10. A low vibration coupled aeroengine high and low pressure turbine layout structure as claimed in claim 1, wherein: the turbine inter-stage bearing frame (B) comprises a bearing seat (B1), a bearing cone shell (B2) and a bearing radials (B3), wherein the radial inner side of the bearing seat (B1) is connected with an outer ring of the rear supporting point (7), and the radial outer side of the bearing seat (B1) is fixedly connected with a plurality of the bearing radials (B3) through the bearing cone shell (B2).
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| CN113123881A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN113833573A (en) * | 2020-06-24 | 2021-12-24 | 中国航发商用航空发动机有限责任公司 | Double-rotor double-branch ignition gas turbine |
| CN115126601A (en) * | 2021-03-26 | 2022-09-30 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
-
2023
- 2023-03-29 CN CN202310318033.XA patent/CN116044569A/en active Pending
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| US8402741B1 (en) * | 2012-01-31 | 2013-03-26 | United Technologies Corporation | Gas turbine engine shaft bearing configuration |
| CN208396759U (en) * | 2018-07-02 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of turbine rear casing and the outer coupling structure for containing force bearing ring |
| CN208564655U (en) * | 2018-07-02 | 2019-03-01 | 中国航发沈阳发动机研究所 | A kind of turbine rear casing coupling structure |
| CN113123876A (en) * | 2019-12-30 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Aircraft engine without turbine rear case structure |
| CN113123881A (en) * | 2019-12-31 | 2021-07-16 | 中国航发商用航空发动机有限责任公司 | Support structure of engine |
| CN113833573A (en) * | 2020-06-24 | 2021-12-24 | 中国航发商用航空发动机有限责任公司 | Double-rotor double-branch ignition gas turbine |
| CN115126601A (en) * | 2021-03-26 | 2022-09-30 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
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