CN214118265U - Turbine and aircraft engine - Google Patents
Turbine and aircraft engine Download PDFInfo
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- CN214118265U CN214118265U CN202023222295.7U CN202023222295U CN214118265U CN 214118265 U CN214118265 U CN 214118265U CN 202023222295 U CN202023222295 U CN 202023222295U CN 214118265 U CN214118265 U CN 214118265U
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Abstract
The utility model relates to a turbine and aeroengine for alleviate the wearing and tearing problem of rotor and stator. Wherein the turbine includes a casing; the wheel disc is arranged in the casing; the first end of the stator is connected with the casing, and the second end of the stator extends towards the wheel disc; the first end of the rotor is connected with the wheel disc, and the second end of the rotor extends towards the casing; the rotor is arranged adjacent to the stator; the first fitting piece is annular and is provided with a comb tooth structure, the first fitting piece is arranged on a first mounting surface of the wheel disc, and the first mounting surface is close to the stator; and the second fitting piece is annular and is provided with a honeycomb structure, the second fitting piece is arranged on a second mounting surface of the stator, the second mounting surface is close to the rotor, the second fitting piece and the first fitting piece are coaxially arranged, and the honeycomb structure is configured to allow the second fitting piece to be in collision and abrasion with the comb tooth structure so as to avoid the collision and abrasion of the stator and the rotor. The utility model discloses can effectively reduce the rotor and stator and bump the risk that the mill brought, avoid arousing the trouble.
Description
Technical Field
The utility model relates to an aerospace equipment field especially relates to a turbine and aeroengine.
Background
Aircraft engine turbine components are in a harsh operating environment for high temperature and high pressure combustion gases. The stator casing is close to the main flow and has high temperature; the rotor shaft is arranged in the center of the engine, and the temperature is low; overall, the stator is at a higher temperature than the rotor. During operation, both the rotor and stator expand backwards (counter-heading) relative to the thrust bearing. But due to the higher temperature of the stator, the expansion amount is larger than that of the rotor. Therefore, after the engine is operated, the distance between the turbine guide vane and the following movable vane is reduced, and the rotor and the stator are easy to rub. The low-pressure turbine is arranged at the rear end of the engine, the axial position of the stator is influenced by the gas compressor, the combustion chamber and the high-pressure turbine, and the rotor and the stator are particularly exposed to collision and abrasion.
Disclosure of Invention
Some embodiments of the utility model provide a turbine and aeroengine for alleviate the wearing and tearing problem of rotor and stator.
Some embodiments of the utility model provide a turbine, a serial communication port, include:
a case;
the wheel disc is arranged in the casing;
the first end of the stator is connected with the casing, and the second end of the stator extends towards the wheel disc;
the first end of the rotor is connected with the wheel disc, and the second end of the rotor extends towards the casing; the rotor is arranged adjacent to the stator;
the first fitting piece is annular and provided with a comb tooth structure, the first fitting piece is arranged on a first mounting surface of the wheel disc, and the first mounting surface is close to the stator; and
the second fitting piece is annular and is provided with a honeycomb structure, the second fitting piece is arranged on a second mounting surface of the stator, the second mounting surface is close to the rotor, the second fitting piece and the first fitting piece are coaxially arranged, and the honeycomb structure is configured to allow the comb tooth structure to be rubbed and abraded so as to avoid the rubbing and abrasion of the stator and the rotor.
In some embodiments, the sealing device further comprises a sealing ring, the sealing ring is arranged at the second end of the stator, and the second mounting surface is arranged on the sealing ring.
In some embodiments, the second fitting member has a honeycomb structure on the whole annular surface, or a plurality of honeycomb structures are arranged on the whole annular surface of the second fitting member at intervals.
In some embodiments, the plurality of honeycombs is uniformly or non-uniformly spaced about the central axis of the second mating member.
In some embodiments, a groove is formed between two adjacent honeycomb structures in the plurality of honeycomb structures, and the groove is an arc-shaped groove or a square-shaped groove.
In some embodiments, the entire annular surface of the first fitting member is provided with the grid structure, or the entire annular surface of the first fitting member is provided with a plurality of grid structures at intervals.
In some embodiments, the plurality of labyrinth structures are evenly spaced or unevenly spaced about the central axis of the second mating member.
In some embodiments, the grate structure has a wear resistance greater than the honeycomb structure.
In some embodiments, the first mating member and the second mating member satisfy the following relationship: a + b is c-d, wherein a is the distance between the comb structure on the first fitting piece and the honeycomb structure on the second fitting piece in the assembled state, and b is the size of the comb structure inserted into the honeycomb structure after the stator and the rotor run for a set time; c is the distance between the grid structure on the first fitting piece and the first mounting surface in the assembled state; d is the distance between the grate structure on the first fitting piece and the first mounting surface after the stator and the rotor run for a set time.
Some embodiments of the present invention provide an aircraft engine comprising a turbine as described above.
Based on the technical scheme, the utility model discloses following beneficial effect has at least:
in some embodiments, one side that closes on the stator at the rotor is equipped with first fitting piece, first fitting piece is equipped with the labyrinth structure, one side that closes on the rotor at the stator is equipped with the second fitting piece, the second fitting piece is equipped with honeycomb, in turbine working process, axial float takes place for rotor and stator, the axial distance of stator and rotor diminishes, the first fitting piece that sets up on the rotor allows to take place to bump with the second fitting piece that sets up on the stator and grinds, the labyrinth structure in the second fitting piece can allow the labyrinth structure on the first fitting piece to insert, can effectually reduce the risk that the rotor bumped and grinds and bring, avoid arousing the trouble.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without undue limitation to the invention. In the drawings:
fig. 1 is a partial schematic view of a turbine provided in accordance with some embodiments of the present invention;
FIG. 2 is a partial schematic view of FIG. 1;
fig. 3 is a schematic view of a second fitting member provided according to a first embodiment of the present invention;
fig. 4 is a schematic side view of a second mating member provided in accordance with a first embodiment of the present invention;
fig. 5 is a schematic side view of a second mating member according to a second embodiment of the present invention;
fig. 6 is a schematic side view of a first mating member provided in accordance with some embodiments of the present invention;
fig. 7 is a schematic diagram of the second mating member mating with the first mating member according to some embodiments of the present invention.
The reference numbers in the drawings illustrate the following:
1-a casing; 2-a wheel disc; 3-a stator; 4-a rotor; 5-a first mating member; 51-a labyrinth structure; 6-a second mating member; 61-honeycomb structure; 7-sealing ring; 8-support ring.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are only some of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the invention.
As shown in fig. 1, some embodiments provide a turbine that includes a casing 1, a disk 2, a stator 3, a rotor 4, a first fitting 5, and a second fitting 6.
The wheel disc 2 is arranged in the casing 1. The first end of stator 3 is connected with casing 1, and the second end of stator 3 extends to rim plate 2. A first end of the rotor 4 is connected to the disk 2 and a second end of the rotor 4 extends towards the casing 1. The rotor 4 is disposed adjacent to the stator 3.
The first fitting piece 5 is annular and provided with a comb structure 51, and the first fitting piece 5 is arranged on a first mounting surface of the wheel disc 2, and the first mounting surface is close to the stator 3. The labyrinth 51 is convex toward the rotor 4 with respect to the stator 3.
The second fitting member 6 is annular and has a honeycomb structure 61 formed thereon, and the second fitting member 6 is provided on a second mounting surface of the stator 3, the second mounting surface being adjacent to the rotor 4. The honeycomb structure 61 is convex toward the stator 3 with respect to the rotor 4.
The second fitting member 6 is disposed coaxially with the first fitting member 5, the second fitting member 6 is configured to allow rubbing against the first fitting member 5, that is, the honeycomb structure 61 is configured to allow rubbing against the comb structure 51, and the comb structure 51 is inserted into the honeycomb structure 61 to prevent rubbing against the stator 3 and the rotor 4.
Be equipped with second fitting piece 6 in one side that stator 3 closes on rotor 4, second fitting piece 6 is equipped with honeycomb structure 61, one side that rotor 4 closes on stator 3 is equipped with first fitting piece 5, first fitting piece 5 is equipped with labyrinth structure 51, in turbine working process, rotor 4 takes place the axial float with stator 3, stator 3 diminishes with rotor 4's axial distance, first fitting piece 5 that sets up on rotor 4 takes place to rub with second fitting piece 6 that sets up on stator 3 earlier, honeycomb structure 61 in the second fitting piece 6 can hold labyrinth structure 51 on the first fitting piece 5, can insert the degree of depth in the honeycomb structure 61 according to labyrinth structure 51, distance between calibration rotor 4 and the stator 3, rub with effectively reducing rotor 4 and stator 3's the mill, avoid rotor 4 and stator 3 to rub the risk that brings and the trouble that arouses.
In some embodiments, the first fitting member 5 is provided with a comb structure 51, the second fitting member 6 is provided with a honeycomb structure 61, the axial honeycomb structure 61 is provided on the rear side of the stator 3, and the comb structure 51 is provided at a corresponding position on the front side of the rotor 4. The honeycomb structure 61 is a porous structure and is soft in texture. In the working process of the turbine, the rotor 4 and the stator 3 axially move, and the axial distance between the stator 3 and the rear rotor 4 is reduced. The honeycomb structure 61 on the stator 3 allows for rub-in with the labyrinth 51 on the rotor 4 without causing failure.
In some embodiments, the turbine further comprises a sealing ring 7, the sealing ring 7 being provided at the second end of the stator 3, the second mounting surface being provided on the sealing ring 7.
In some embodiments, the turbine further comprises a support ring 8, the support ring 8 being provided at the second end of the stator 3, and the sealing ring 7 being provided at the support ring 8.
In some embodiments, as shown in fig. 3, the second fitting member 6 has a circular ring shape, and the honeycomb structure 61 is provided on an end surface of the second fitting member 6 adjacent to the rotor 4.
In some embodiments, the honeycomb structure 61 is provided on the entire annular surface of the second fitting member 6.
In some embodiments, as shown in fig. 3 to 5, the second mating member 6 is provided with a plurality of honeycombs 61 spaced throughout the annular face thereof.
In some embodiments, the plurality of honeycombs 61 are uniformly or non-uniformly spaced about the central axis of the second mating member 6.
In some embodiments, a groove is formed between two adjacent honeycomb structures 61 in the plurality of honeycomb structures 61, and the groove is an arc-shaped groove, as shown in fig. 5, and the honeycomb structures 61 are wavy honeycomb structures. Alternatively, the grooves are square grooves, as shown in fig. 4.
In some embodiments, as shown in fig. 6, the comb structure 51 extends toward the second fitting 6, and optionally, the length of the comb structure 51 extends perpendicular to the direction between the first end and the second end of the rotor 4 and the central axis of the disk 2.
In some embodiments, the first fitting member 5 is provided with a grate structure 51 on the whole annular surface.
In some embodiments, as shown in fig. 6, the first fitting member 5 has a plurality of grate structures 51 spaced on the whole annular surface.
In some embodiments, the plurality of labyrinth structures 51 are uniformly spaced or non-uniformly spaced around the central axis of the second mating member 6.
One side that closes on rotor 4 at stator 3 is equipped with second fitting piece 6, and second fitting piece 6 is equipped with honeycomb structure 61, and one side that closes on stator 3 at rotor 4 is equipped with first fitting piece 5, and first fitting piece 5 is equipped with comb tooth structure 51, and first fitting piece 5 takes place to bump with the cooperation of second fitting piece 6 and grinds, slows down bumping of rotor 4 and stator 3 and grinds.
If sealing is required, the entire annular surface of the first fitting part 5 is provided with the labyrinth 51, and the entire annular surface of the second fitting part 6 is provided with the honeycomb 61, which serves as sealing.
If no sealing is required here, the first fitting part 5 is provided with a plurality of grid structures 51 at intervals on the whole annular surface, i.e. the grid structures 51 are discontinuous in the circumferential direction, and/or the second fitting part 6 is provided with a plurality of honeycomb structures 61 at intervals on the whole annular surface, i.e.: circumferentially discontinuous honeycomb 61 to allow airflow.
In some embodiments, the wear resistance of the grate structure 51 is greater than the wear resistance of the honeycomb structure 61. The honeycomb structure 61 is a porous structure and is soft in texture.
In some embodiments, as shown in fig. 2 and 7, the first fitting member 5 and the second fitting member 6 satisfy the following relationship: a + b is c-d, wherein a is the distance between the comb structure 51 of the first fitting piece 5 and the honeycomb structure 61 of the second fitting piece 6 in the assembled state, and b is the dimension of the comb structure 51 inserted into the honeycomb structure 61 after the stator 3 and the rotor 4 run for a set time, and the dimension is obtained by measuring with a tool ruler; c is the distance between the grate structure 51 of the first fitting piece 5 and the first mounting surface in the assembled state; d is the distance between the comb-tooth structure 51 of the first fitting piece 5 and the first installation surface after the stator 3 and the rotor 4 are operated for a set time.
The dimensions of a and c are adjusted according to a + b-c-d, and d, d-c- (a + b), i.e. the minimum axial distance between the rotor 4 and the stator 3 in the working state, can be obtained after the test. Under the condition that d meets the set condition, the rotor 4 and the stator 3 cannot be in collision and abrasion, and the comb tooth structure 51 and the honeycomb structure 61 are in collision and abrasion.
In some embodiments, the cold clearance of the rotor 4 and the stator 3 may be measured first when the rotor 4 and the stator 3 are assembled. After the engine finishes the test, decompose rotor 4 and stator 3, measure the bump and rub the degree of depth of honeycomb on stator 3 through the instrument chi, can indirectly obtain the minimum axial distance of rotor 4 and stator 3 in the course of the work. The minimum axial distance is obtained by actual rubbing depth of the rotor 4 and the stator 3, because rubbing risk exists between the rotor 4 and the stator 3, and because the internal environment temperature of the turbine is high, the axial clearance measurement is difficult by using a sensor, and the method for measuring the axial clearance in the working process of the rotor and the stator by using the tool ruler is more reliable than calculation simulation and sensor measurement.
In some embodiments, the turbine rotor axial anti-collision structure composed of the first fitting piece 5 and the second fitting piece 6 may be disposed between the stage one guide vane and the stage one movable vane of the low-pressure turbine. This position is a high risk zone of rub-in of the rotor 4 with the stator 3. But is not limited to being disposed therein.
For example, in some embodiments, as shown in fig. 1, the first stage vanes (stator 3) of the low pressure turbine are suspended from the casing 1 while being clamped, supported by the support ring 8. The primary movable blades (rotors 4) are fixedly arranged on the primary turbine disc 2. A second fitting piece 6 is welded on the rim sealing ring 7 of the first-stage guide vane, a honeycomb structure 61 is arranged on the second fitting piece 6, a first fitting piece 5 is arranged on the first-stage turbine disc 2, and a labyrinth structure 51 is arranged on the first fitting piece 5. The cold-state axial clearance between the honeycomb structure 61 and the grate structure 51 is the minimum distance between the first-stage guide vane and the first-stage movable vane.
When the engine works, the axial distance between the first-stage guide vane and the first-stage movable vane is reduced, and the first-stage guide vane and the first-stage movable vane are firstly rubbed and ground at the honeycomb structure 61 and the grate structure 51. When the operation is stopped, the low-pressure turbine is decomposed and checked, and the rubbing depth of the honeycomb structure 61 and the comb tooth structure 51 is checked and measured. The minimum axial distance between the first-stage guide vane and the first-stage movable vane during the running process of the engine can be calculated according to the method. When the engine is tested next time, the rim sealing ring can be replaced, and the axial clearance data of the rotor and the stator for multiple times can be obtained, so that the accurate minimum distance between the first-stage guide vane and the first-stage movable vane can be obtained and the minimum distance can be used for guiding the subsequent installation. The data is obtained by measuring the actual rubbing depth of the rotor and the stator, namely, the rubbing depth of the honeycomb structure 61 and the comb tooth structure 51, and is more reliable than the calculation simulation or the sensor measurement.
When the turbine rotor stator axial anti-collision structure composed of the first fitting piece 5 and the second fitting piece 6 is applied to the first-stage guide vane and the first-stage movable vane, the labyrinth on the first-stage wheel disc can be set to be a whole-ring structure, and a honeycomb labyrinth sealing pair is formed at the position, so that the backflow of mainstream gas can be reduced.
Some embodiments provide an aircraft engine comprising a turbine as described above.
Based on the above embodiments of the present invention, the technical features of one of the embodiments can be advantageously combined with one or more other embodiments without explicit negatives.
In the description of the present invention, it should be understood that the terms "first", "second", "third", etc. are used to define the components, and are only used for the convenience of distinguishing the components, and if not stated otherwise, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present invention.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and not for limiting the same; although the present invention has been described in detail with reference to preferred embodiments, it should be understood by those skilled in the art that: the invention can be modified or equivalent substituted for some technical features; without departing from the spirit of the present invention, it should be understood that the scope of the claims is intended to cover all such modifications and variations.
Claims (10)
1. A turbine, comprising:
a casing (1);
the wheel disc (2) is arranged in the casing (1);
a stator (3) having a first end connected to the casing (1) and a second end extending toward the wheel disc (2);
a rotor (4) with a first end connected with the wheel disc (2) and a second end extending towards the casing (1); the rotor (4) is arranged adjacent to the stator (3);
the first fitting piece (5) is annular and provided with a comb tooth structure (51), the first fitting piece (5) is arranged on a first mounting surface of the wheel disc (2), and the first mounting surface is close to the stator (3); and
second fitting piece (6), for the annular, be equipped with honeycomb (61) on it, second fitting piece (6) are located the second installation face of stator (3), the second installation face closes on rotor (4), second fitting piece (6) with first fitting piece (5) coaxial arrangement, honeycomb (61) be configured as allow with comb tooth structure (51) bumps the mill, in order to avoid stator (3) with bumping the mill of rotor (4).
2. The turbine of claim 1, further comprising a seal ring (7), the seal ring (7) being disposed at a second end of the stator (3), the second mounting surface being disposed on the seal ring (7).
3. The turbine according to claim 1, characterized in that the second fitting element (6) is provided with a honeycomb structure (61) over the entire annular surface, or that the second fitting element (6) is provided with a plurality of honeycomb structures (61) spaced over the entire annular surface.
4. The turbine according to claim 3, characterized in that the plurality of honeycombs (61) is arranged evenly or unevenly spaced around the central axis of the second counterpart (6).
5. The turbine of claim 3, wherein a slot is formed between two adjacent honeycombs (61) in the plurality of honeycombs (61), the slot being an arcuate slot or a square slot.
6. The turbine according to claim 1, characterized in that the first fitting member (5) is provided with a plurality of grid structures (51) on the whole annular surface, or the first fitting member (5) is provided with a plurality of grid structures (51) on the whole annular surface at intervals.
7. The turbine according to claim 6, characterized in that the plurality of labyrinth structures (51) are arranged evenly or unevenly spaced around the central axis of the second counterpart (6).
8. The turbine according to claim 1, characterized in that the wear resistance of the grate structure (51) is greater than the wear resistance of the honeycomb structure (61).
9. The turbine according to claim 1, characterized in that said first counterpart (5) and said second counterpart (6) satisfy the following relationship: a + b is c-d, wherein a is the distance between the comb tooth structure (51) on the first fitting piece (5) and the honeycomb structure (61) on the second fitting piece (6) in the assembled state, and b is the size of the comb tooth structure (51) inserted into the honeycomb structure (61) after the stator (3) and the rotor (4) run for a set time; c is the distance between the grate structure (51) on the first fitting piece (5) and the first mounting surface in the assembled state; d is the distance between the grate structure (51) on the first fitting piece (5) and the first mounting surface after the stator (3) and the rotor (4) run for a set time.
10. An aircraft engine, characterised by comprising a turbine according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023222295.7U CN214118265U (en) | 2020-12-28 | 2020-12-28 | Turbine and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023222295.7U CN214118265U (en) | 2020-12-28 | 2020-12-28 | Turbine and aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN214118265U true CN214118265U (en) | 2021-09-03 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202023222295.7U Active CN214118265U (en) | 2020-12-28 | 2020-12-28 | Turbine and aircraft engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115235782A (en) * | 2022-09-21 | 2022-10-25 | 中国航发上海商用航空发动机制造有限责任公司 | Turbine rotor stator axial collision and abrasion detection device and method |
-
2020
- 2020-12-28 CN CN202023222295.7U patent/CN214118265U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115235782A (en) * | 2022-09-21 | 2022-10-25 | 中国航发上海商用航空发动机制造有限责任公司 | Turbine rotor stator axial collision and abrasion detection device and method |
| CN115235782B (en) * | 2022-09-21 | 2023-01-13 | 中国航发上海商用航空发动机制造有限责任公司 | Turbine rotor stator axial collision and abrasion detection device and method |
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