CN111677589A - Composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly - Google Patents
Composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly Download PDFInfo
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- CN111677589A CN111677589A CN202010523620.9A CN202010523620A CN111677589A CN 111677589 A CN111677589 A CN 111677589A CN 202010523620 A CN202010523620 A CN 202010523620A CN 111677589 A CN111677589 A CN 111677589A
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- ring
- nut
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- impact
- gas turbine
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- 238000013016 damping Methods 0.000 title claims abstract description 36
- 239000002131 composite material Substances 0.000 title claims abstract description 17
- 239000002184 metal Substances 0.000 claims description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 230000003139 buffering effect Effects 0.000 abstract description 7
- 230000005540 biological transmission Effects 0.000 abstract description 6
- 230000005284 excitation Effects 0.000 abstract description 4
- 230000002829 reductive effect Effects 0.000 abstract description 4
- 230000003068 static effect Effects 0.000 abstract description 4
- 230000035939 shock Effects 0.000 description 10
- 230000001133 acceleration Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 238000004880 explosion Methods 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 3
- 238000002955 isolation Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000002457 bidirectional effect Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 230000000670 limiting effect Effects 0.000 description 1
Images
Classifications
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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
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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
- F01D25/04—Antivibration arrangements
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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
-
- 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
- F02C6/20—Adaptations of gas-turbine plants for driving vehicles
- F02C6/203—Adaptations of gas-turbine plants for driving vehicles the vehicles being waterborne vessels
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention relates to a composite elastic cantilever type vibration-damping and impact-resisting assembly of a turbine support ring of a gas turbine, in particular to a composite elastic cantilever type vibration-damping and impact-resisting assembly device, which aims to provide a vibration-damping assembly in a turbine support ring structure assembly to realize the vibration-damping function and simultaneously require good impact resistance so as to effectively protect a turbine rotor and isolate the vibration excitation transmission of the rotor. The radial deformation of the rotor support is controlled, dynamic and static gaps are reduced, and the turbine rotor blade is prevented from being rubbed and abraded; the spherical shaft sleeve, the adjusting ring, the group of annular thin plates and the nut are sleeved on the outer side wall of the pipe connecting ring, the tightening piece inner ring is sleeved on the nut, the nut is installed on the inner side wall of the compensator shell, the tightening piece outer ring is located between the nut and the group of annular thin plates, and the flow guide strut is installed between the compensator shell and the pipe connecting ring. The invention is used for the field of anti-seismic buffering.
Description
Technical Field
The invention relates to a composite elastic cantilever type vibration-damping impact-resisting assembly device, in particular to a composite elastic cantilever type vibration-damping impact-resisting assembly for a turbine support ring of a gas turbine, which is used for realizing vibration transmission isolation and impact-resisting protection of a power turbine rotor system of the gas turbine.
Background
With the development of science and technology in recent years, the explosion equivalent and the impact duration are obviously increased, the hit rate is greatly improved due to an accurate computing mechanism, and the threat to the electromechanical equipment of the naval vessel is more and more serious. Meanwhile, with a large amount of equipment of advanced ship-based instruments such as electronic countermeasure, communication navigation and the like, the requirements on the environment are more strict, and the sensitive response of the instrument can lead to long-time out-of-control manipulation due to slight shock wave input. Impact load generated during contact explosion and non-contact explosion of various types of equipment enables the carrier-based electromechanical equipment to lose efficacy when the impact load is light, and enables the naval vessel to break and sink when the impact load is heavy. Therefore, the shock resistance protection capability of the naval vessel and the electromechanical equipment of the naval vessel is improved, and the general tactical performance of the prior novel naval vessel is improved.
In the field of gas turbines for ships, the vertical acceleration shock resistance of an American LM2500 gas turbine is 15g, the frequency of an elastic supporting element is 6Hz, and the gas turbine has a good shock isolation effect. The Soviet Union has obvious difference with the Western on the shock-resistant technical route of the naval vessel electromechanical equipment, and emphasizes the shock resistance level of the equipment. The vertical acceleration shock resistance of the gas turbine body of Ukrainian can reach dozens of g. g is the acceleration of gravity of 9.8 m/s. The turbine part of the gas turbine has high impact resistance requirement when used on a ship, and the structure of the turbine supporting ring vibration-damping impact-resistant assembly device is directly related to the use safety of a unit on the ship. After the impact input of the ship is effectively isolated by the gas turbine isolation system, the impact load of dozens of g is still born after the impact input of the ship is transmitted to the turbine body. The damping assembly in the turbine support ring structure assembly also requires good shock resistance while achieving a damping function to effectively protect the turbine rotor and isolate the rotor vibration excitation transmission. Radial deformation of the rotor support is controlled, dynamic and static gaps are reduced, and collision and abrasion of turbine rotor blades are avoided. Aiming at the characteristics, the invention designs the composite elastic cantilever type gas turbine support ring vibration reduction and impact resistance assembly.
Disclosure of Invention
The invention aims to provide a vibration damping assembly in a turbine supporting ring structure assembly, which realizes the vibration damping function and simultaneously requires good shock resistance so as to effectively protect a turbine rotor and isolate the transmission of rotor vibration excitation. Radial deformation of the rotor support is controlled, dynamic and static gaps are reduced, and collision and abrasion of turbine rotor blades are avoided.
The technical scheme adopted by the invention for solving the problems is as follows:
the compensator comprises an adjusting ring, a spherical shaft sleeve, a nut, a tightening piece, a compensator shell, a nut, a group of annular thin plates, a pipe connecting ring and a flow guide strut; the pipe joint ring is installed in the compensator shell, the spherical shaft sleeve, the adjusting ring, the group of annular thin plates and the nut are sleeved on the outer side wall of the pipe joint ring, the nut is in threaded connection with the pipe joint ring, the tightening part inner ring is sleeved on the nut, the nut is installed on the inner side wall of the compensator shell, the tightening part outer ring is located between the nut and the group of annular thin plates, and the flow guide support is installed between the compensator shell and the pipe joint ring.
The invention has the beneficial effects that:
the compensator housing 5 is located on the entire turbine support ring damping impact assembly device external structural support. A stepped cylindrical rotary structure is adopted, the small caliber of the diversion pillar 10 is transited to the large caliber at the side of the casing to serve as the outer wall of a cylindrical inner cavity, and a connecting piece is fixed on the compensator shell through threads to clamp a group of outer rings of annular thin plates 8; the pipe connection ring 9 adopts a cylindrical stepped cylinder wall structure, supports the inner wall of a cylindrical cavity of the whole turbine support ring vibration-damping and impact-resisting assembly device, and clamps an annular thin plate inner ring. The nut 3 and the rectifying strut 12 are connected to the pipe joint ring 9 and transmit the load between the power turbine support ring flow guiding support plate and the casing.
The nut 3, the tightening element 4 and the nut 6, as described in connection with fig. 1, fasten the inner and outer rings of the elastic sheet from the outside of the power turbine casing. Wherein the nut 3 is in threaded connection with the inner pipe connecting ring 9, and the lower end face of the inner ring of the elastic sheet is restrained and clamped by screwing and extruding the spherical shaft sleeve 2 through the nut 3. The tightening piece 4 adopts a bent bowl-shaped structure, the inner ring is connected with the nut 3, and the outer ring compresses the bearing ring 7. The nut 6 is connected to the inner surface of the compensator shell 5 through a screw thread on the side of the casing, and the outer ring of the elastic sheet is restrained and clamped through screwing and extruding the outer ring of the tightening piece 4, so that the functions of laterally adjusting the depth of the cylindrical cavity and screwing and fixing are achieved.
The set of annular sheets 8 described with reference to fig. 1 and 2 is in the form of a clamping cantilever, and the inner ring and the outer ring of the annular structure are respectively clamped and fixed, the inner ring moves in conjunction with the fairing columns 12, and the outer ring is structurally connected to the turbine casing 11 of the gas turbine power. Through the design of the clamped cantilever structure, the bidirectional buffering and isolating load is ensured through the tensile compression elastic structure of materials instead of the traditional rubber and the like, and the use limitation of elastic components such as rubber and the like under the high-temperature condition is avoided. Meanwhile, enough rigidity is provided in the axial direction and the circumferential direction, and the effects of radial buffering and axial and circumferential constraint limiting are achieved. Therefore, the structural strength and the reliability of the turbine support ring vibration-damping and impact-resisting assembly under the high-temperature working condition are ensured. The impact load is transmitted along the paths of the turbine casing 11, the outer ring of the annular thin plate 8, the inner ring of the annular thin plate 8, the rectifying struts 12, the bearing housing 13 and the rotor system 14, and the rotor vibration load is excited and transmitted along the opposite direction of the paths. The dynamic characteristics of the turbine support ring vibration-damping and impact-resisting assembly are adjusted by adjusting the material, the quantity and the thickness of the thin plates. Through the cantilever structural design of centre gripping, play in radial buffering, the spacing effect of axial and circumference restraint. The annular cantilever structure of the thin plate generates enough composite buffering counter force through bending deformation, so that the supporting ring meets the acceleration response requirement under the bidirectional deformation of vibration impact stretching and compression.
The gas turbine supporting ring vibration-damping and impact-resisting component device with the cantilever structure is designed aiming at vibration damping and impact resistance of a gas turbine device, is used for realizing the effects of resisting underwater explosion impact transmitted to a turbine rotor system by the gas turbine device and inhibiting the excitation load transmission of the turbine rotor, and bears the buffering and vibration transmission of the turbine rotor system of the gas turbine device to influence the vertical/transverse/longitudinal impact acceleration response and vibration acceleration level; the annular thin plates 8 are fixedly clamped by adopting a cantilever structure, the damping and rigidity characteristics of the support ring vibration-damping and impact-resisting assembly device are ensured by adjusting the material, the thickness and the number of the group of annular thin plates 8, and the support ring vibration-damping and impact-resisting assembly device has larger elastic force and provides elastic-damping buffering for the support deformation of the turbine rotor system bearing. Radial deformation of the rotor support is controlled, dynamic and static gaps are reduced, and collision and abrasion of turbine rotor blades are avoided.
The group of annular thin plates 8 adopt a clamping type fixing structure, so that the circumferential and axial freedom degrees of the elastic thin plates are restricted in a limited volume space; the elastic thin plate is fastened to support the cantilever, the space of the radial cylindrical cavity is adjusted, the thickness and the number of the elastic thin plate are further controlled, the structural strength and the quality of the rotor are combined, and the rigidity and the damping of the support ring vibration-damping and impact-resisting assembly device are optimized, so that the effect of improving the vibration-damping and impact-resisting performance of the gas turbine device is achieved.
Drawings
Fig. 1 is a schematic view of the overall structure of the present application.
FIG. 2 is a schematic view of the present application mounted on a power turbine support ring for shock absorption and impact resistance.
Detailed Description
The first embodiment is as follows: the embodiment is described with reference to fig. 1-2, and the composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly of the embodiment comprises an adjusting ring 1, a spherical shaft sleeve 2, a nut 3, a tightening piece 4, a compensator shell 5, a nut 6, a group of annular thin plates 8, a pipe joint ring 9 and a flow guide strut 10; the pipe joint ring 9 is installed in compensator casing 5, spherical surface axle sleeve 2, adjusting ring 1, 3 covers of a set of annular sheet metal 8 and nut are established on the lateral wall of pipe joint ring 9, and nut 3 and 9 threaded connection of pipe joint ring, it suits on nut 3 to tighten 4 inner ring suits of piece, nut 6 is installed on compensator casing 5's inside wall, it is located between nut 6 and a set of annular sheet metal 8 to tighten 4 outer rings of piece, water conservancy diversion pillar 10 is installed between compensator casing 5 and pipe joint ring 9.
The second embodiment is as follows: the embodiment is described with reference to fig. 1-2, and the composite elastic cantilever type gas turbine support ring vibration damping and impact resisting assembly of the embodiment is formed by combining and stacking a plurality of annular thin plates 8, and the rest is the same as the first embodiment.
The third concrete implementation mode: the embodiment is described with reference to fig. 1-2, and the composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly of the embodiment further comprises a pressure-bearing ring 7, wherein the pressure-bearing ring 7 is installed between the tightening piece 4 and a group of annular thin plates 8. The pressure ring acts to support the outer ring of the set of annular sheets 8 and to clamp the outer ring of elastic sheets between the constriction 4 and the set of annular sheets 8.
The fourth concrete implementation mode: the embodiment is described with reference to fig. 1-2, and the tightening member 4 is a bowl-shaped structure to increase the flexibility and deformation capability of the tightening member.
The fifth concrete implementation mode: the embodiment is described with reference to fig. 1-2, and the composite elastic cantilever type gas turbine support ring vibration damping and impact resisting assembly according to the embodiment is characterized in that an annular boss is arranged outside a pipe joint ring 9, a spherical shaft sleeve 2, an adjusting ring 1, a group of annular thin plates 8 and a nut 6 are sequentially sleeved outside the pipe joint ring 9, the spherical shaft sleeve 2 abuts against the annular boss of the pipe joint ring 9, and the nut 6 is installed on the pipe joint ring 9 in a threaded connection manner. The nut 3, the tightening element 4 and the nut 6 serve as the outer side of the power turbine casing to tighten the inner and outer rings of the annular sheet 8. Wherein the nut 3 is in threaded connection with the pipe joint ring 9, and the spherical shaft sleeve 2 is extruded by screwing the nut 3 so as to restrict and clamp a group of annular thin plates 8. The inner ring of the tightening part is connected with the nut 3, the annular thin plate 8 compresses the bearing ring 7, and the tightening part 4 adopts a bent bowl-shaped structure to increase the deflection deformation capacity of the tightening part 4. The nut 6 is connected to the inner surface of the compensator shell through a casing side thread, the outer ring of the tightening part 4 is tightly screwed and extruded through the screwing nut 3, the outer ring of the annular thin plate 8 is restrained and clamped, and the depth of the cylindrical cavity is adjusted and the cylindrical cavity is tightly screwed and fixed on the outer side of the power turbine casing. The two sides of a group of annular thin plates 8 are clamped by the annular bosses of the pipe connecting ring 9 and the nuts 3, and the pipe connecting ring 9 and the annular bosses outside the pipe connecting ring 9 support the inner wall of a cylindrical cavity of the whole turbine support ring vibration-damping impact-resisting assembly device and bear main structural strength load. The nut 3 and the flow guide support column 10 are connected to a pipe connecting ring 9, and the relative movement of the pipe connecting ring 9 applies acting force to a group of annular thin plates 8 by pushing the adjusting ring 1 and the spherical shaft sleeve 2 to transfer load between the flow guide support plate and the casing of the power turbine support ring. The rest is the same as the first embodiment.
Claims (5)
1. The composite elastic cantilever type turbine support ring vibration-damping and impact-resisting component of the gas turbine is characterized in that: the compensator comprises an adjusting ring (1), a spherical shaft sleeve (2), a nut (3), a tightening piece (4), a compensator shell (5), a nut (6), a group of annular thin plates (8), a pipe connecting ring (9) and a flow guide strut (10); pipe joint ring (9) is installed in compensator casing (5), spherical surface axle sleeve (2), adjusting ring (1), a set of annular sheet metal (8) and nut (3) cover are established on the lateral wall of pipe joint ring (9), and nut (3) and pipe joint ring (9) threaded connection, it installs on nut (3) to tighten piece (4) inner ring suit, nut (6) are installed on the inside wall of compensator casing (5), it is located between nut (6) and a set of annular sheet metal (8) to tighten piece (4) outer loop, water conservancy diversion pillar (10) are installed between compensator casing (5) and pipe joint ring (9).
2. The composite elastic cantilevered gas turbine support ring vibration damping and impact resistant assembly of claim 1 wherein: the group of annular thin plates (8) is formed by combining and superposing a plurality of annular thin plates (8).
3. The composite elastic cantilevered gas turbine support ring vibration damping and impact resistant assembly of claim 1 wherein: it also comprises a bearing ring (7), the bearing ring (7) is arranged between the tightening piece (4) and a group of annular thin plates (8).
4. The composite elastic cantilevered gas turbine support ring vibration damping and impact resistant assembly of claim 1 wherein: the tightening piece (4) is of a bowl-shaped structure, and the deflection deformation capacity of the tightening piece is improved.
5. The composite elastic cantilevered gas turbine support ring vibration damping and impact resistant assembly of claim 1 wherein: the outside of the pipe joint ring (9) is provided with an annular boss, the spherical shaft sleeve (2), the adjusting ring (1), the group of annular thin plates (8) and the nut (6) are sequentially sleeved outside the pipe joint ring (9), the spherical shaft sleeve (2) is pressed against the annular boss of the pipe joint ring (9), and the nut (6) is connected with the pipe joint ring (9) in a threaded manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010523620.9A CN111677589A (en) | 2020-06-10 | 2020-06-10 | Composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010523620.9A CN111677589A (en) | 2020-06-10 | 2020-06-10 | Composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly |
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| Publication Number | Publication Date |
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| CN111677589A true CN111677589A (en) | 2020-09-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010523620.9A Pending CN111677589A (en) | 2020-06-10 | 2020-06-10 | Composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114233398A (en) * | 2021-12-13 | 2022-03-25 | 中国船舶重工集团公司第七0三研究所 | Composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly device |
| CN114575946A (en) * | 2022-03-09 | 2022-06-03 | 中国船舶重工集团公司第七0三研究所 | Anti-loosening structure for positioning pin of primary clapboard retaining ring |
-
2020
- 2020-06-10 CN CN202010523620.9A patent/CN111677589A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114233398A (en) * | 2021-12-13 | 2022-03-25 | 中国船舶重工集团公司第七0三研究所 | Composite elastic cantilever type gas turbine support ring vibration-damping and impact-resisting assembly device |
| CN114575946A (en) * | 2022-03-09 | 2022-06-03 | 中国船舶重工集团公司第七0三研究所 | Anti-loosening structure for positioning pin of primary clapboard retaining ring |
| CN114575946B (en) * | 2022-03-09 | 2023-12-05 | 中国船舶重工集团公司第七0三研究所 | Locating pin anti-loosening structure of first-stage baffle holding ring |
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