CN115163311A - High-temperature metal sealing ring of small gas turbine - Google Patents
High-temperature metal sealing ring of small gas turbine Download PDFInfo
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- CN115163311A CN115163311A CN202210854808.0A CN202210854808A CN115163311A CN 115163311 A CN115163311 A CN 115163311A CN 202210854808 A CN202210854808 A CN 202210854808A CN 115163311 A CN115163311 A CN 115163311A
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- sealing ring
- sealing
- matching surface
- temperature
- stress relief
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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
- F02C7/28—Arrangement of seals
Abstract
The invention relates to a high-temperature metal sealing ring of a small-sized gas turbine, which comprises: the sealing ring, the sealing matching surface and the stress relief groove; the sealing matching surface comprises a first matching surface and a second matching surface, and the stress relief groove is arranged on the inner side of the sealing ring. The invention has the beneficial effects that: the stress relief groove is arranged to absorb high-temperature expansion, and when the temperature is changed from low temperature to high temperature, the expansion direction points to the direction of reducing the stress relief groove, so that the stress concentration caused by high-temperature expansion is effectively solved, and the service life of the metal sealing ring under the high-temperature condition is prolonged; the width of the stress relief groove is set as the annular expansion amount of the sealing ring at the working temperature of the sealing ring, and the stress relief groove is just closed during normal working, so that the sealing effect in a high-temperature environment is effectively improved; the sealing device is provided with sealing matching surfaces with the surface roughness not greater than Ra0.8 and the free space being 1.005-1.01 times of the width of the sealing groove, thereby ensuring that the sealing device is plane-sealed when in use, realizing sealing by using pressure difference and improving the sealing effect.
Description
Technical Field
The invention belongs to the field of sealing devices, and particularly relates to a high-temperature metal sealing ring of a small gas turbine.
Background
The gas turbine is used as an internal combustion type power machine which takes continuous flowing gas as working medium to drive an impeller to rotate so as to convert chemical energy into work, and comprises three large core parts: a compressor, a combustion chamber and a gas turbine. The blades of the gas turbine are mounted on a turbine disk, the turbine disk of a small gas turbine is generally connected by face teeth, the face teeth have large tooth gaps, large flow leakage is generated at the tooth tops and the tooth bottoms, the turbine disk is used as a high-temperature component, the leakage can cause uncontrollable cooling gas distribution, and therefore the sealing of the position needs to be considered independently. Meanwhile, the sealing ring and the sealing groove cannot have a large gap for remaining allowance for expansion, otherwise hidden dangers in aspects such as vibration and the like can be brought when the sealing ring rotates at a high speed, if the gap is insufficient, the metal sealing ring can be extruded with the sealing groove when being heated and expanded, obvious stress concentration is generated, the service life of the metal sealing ring is influenced, and the turbine disc and the like can be damaged by the sealing element, so that the service life of the metal sealing ring is influenced.
Sealing is generally performed by installing a sealing ring, CN112780772A discloses a U-shaped metal sealing ring; CN213775537U all discloses a metal sealing ring, is applied to between gate valve disk seat and the valve body is opened the shelves, can't be used for sealing between the gas turbine dish, and can't be applied to the higher condition that reaches more than 500 ℃. CN213775537U discloses a special-shaped section metal sealing ring, but does not describe the situation that can be used for turbine side sealing and high temperature application.
In summary, the existing sealing ring can not be used for sealing between turbine disks of a gas turbine and can not be applied to the condition that the temperature is higher and reaches more than 500 ℃.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a high-temperature metal sealing ring of a small gas turbine.
The high-temperature metal sealing ring of the small gas turbine comprises a sealing ring, a sealing matching surface and a stress relief groove; the sealing matching surface comprises a first matching surface and a second matching surface, the first matching surface and the second matching surface are respectively arranged on the upper surface and the lower surface of the sealing ring, and the annular section of the sealing ring between the first matching surface and the second matching surface is in an arc shape concave to the center of the sealing ring; the destressing groove is arranged on the inner side of the sealing ring, the depth direction of the destressing groove is perpendicular to the ring shape, and the surface of the deepest part of the destressing groove is arc-shaped.
Preferably, the method comprises the following steps: the sealing ring is provided with a plurality of stress relief grooves, and the number of the stress relief grooves is less than or equal to 4.
Preferably, the method comprises the following steps: the width L of the stress relief grooves is determined by the diameter expansion amount of the sealing ring in high-temperature work, and the sum of the widths L of all the stress relief grooves is equal to or smaller than the diameter expansion amount of the sealing ring.
Preferably, the method comprises the following steps: the sealing ring is made of high-temperature alloy material; the surface roughness of the first matching surface and the second matching surface is not more than Ra0.8, and the free distance between the first matching surface and the second matching surface is 1.005-1.01 times of the width of the sealing groove.
Preferably, the method comprises the following steps: the first matching surface and the second matching surface are provided with lead-in chamfers.
Preferably, the method comprises the following steps: the sealing ring is manufactured by adopting integrated machining.
The use method of the high-temperature metal sealing ring of the small gas turbine comprises the following steps:
step, engaging a turbine disk: the first turbine disc and the second turbine disc are meshed and connected with each other through end face teeth;
step, installing a sealing ring: installing a sealing ring in a sealing groove between a first turbine disc and a second turbine disc, and respectively pressing two sides of the sealing groove by a first matching surface and a second matching surface;
step, gas turbine work: high-temperature gas generated by a small gas turbine is arranged above the first wheel disc and the second turbine disc to push the blades to do work, a gas path of cooling gas is arranged below the first turbine disc and the second turbine disc, the gas pressure P1 of the cooling gas below is higher than the gas pressure P2 of the high-temperature gas above, and the first matching surface and the second matching surface are more attached to the surfaces of the sealing grooves; and the metal sealing ring expands and becomes larger along with the rise of the temperature, and the width L of the stress relief groove becomes narrower.
The invention has the beneficial effects that:
1) The invention is provided with the destressing groove so as to absorb the high-temperature expansion amount, when the temperature of the metal sealing ring is changed from low temperature to high temperature, the expansion direction of the metal sealing ring points to the direction of reducing the destressing groove, the problem of stress concentration caused by high-temperature expansion of the metal sealing ring is effectively solved, and the service life of the metal sealing ring under the high-temperature condition is prolonged.
2) The width of the stress relief groove is set to be the annular expansion amount of the sealing ring at the working temperature of the sealing ring, so that the stress relief groove is just closed due to thermal expansion of the sealing ring during normal working, leakage-free sealing is realized, and the sealing effect in a high-temperature environment is effectively improved.
3) The invention is provided with two side sealing matching surfaces, the surface roughness is not more than Ra0.8, and the free distance between the two matching surfaces is 1.005-1.01 times of the width of the sealing groove, thereby ensuring that the sealing ring is in a pressing state when in use, realizing plane sealing, realizing sealing by utilizing pressure difference and improving the sealing effect.
Drawings
FIG. 1 is a general schematic view of a high temperature metal seal ring;
FIG. 2 is a schematic cross-sectional view of a high temperature metal seal ring;
FIG. 3 is a schematic view of a high temperature metal seal ring stress relief groove at position A in FIG. 1;
fig. 4 is a schematic view of an application scenario of the high-temperature metal sealing ring.
Description of reference numerals: the sealing matching surface 1, the matching surface I2, the matching surface II 3, the stress relief groove 4, the turbine disc I5, the turbine disc II 6 and the end face teeth 7.
Detailed Description
The present invention will be further described with reference to the following examples. The following examples are set forth merely to aid in the understanding of the invention. It should be noted that, for a person skilled in the art, several modifications can be made to the invention without departing from the principle of the invention, and these modifications and modifications also fall within the protection scope of the claims of the present invention.
Example one
As an example, as shown in fig. 1 to 3: a high-temperature metal sealing ring of a small-sized gas turbine is made of high-temperature alloy materials through integrated machining and comprises a sealing ring, a sealing matching surface 1 and a stress relief groove 4; the required precision of the sealing matching surface 1 is high, and the surface roughness is not more than Ra0.8; the sealing matching surface 1 comprises a first matching surface 2 and a second matching surface 3, the first matching surface 2 and the second matching surface 3 are respectively arranged on the upper surface and the lower surface of the sealing ring and provided with lead-in chamfers, so that the installation is convenient; the free distance between the first matching surface 2 and the second matching surface 3 is 1.005-1.01 times of the width of the sealing groove, and the ring section of the sealing ring is in an arc shape concave to the center of the sealing ring;
the inner side of the sealing ring is provided with no more than 4 stress relief grooves 4, the depth direction of each stress relief groove 4 is perpendicular to the ring shape, and the innermost surface of each stress relief groove 4 is in an arc shape; the width L of the stress relieving groove is set based on the temperature of the position when the small-sized gas turbine normally operates, and is determined by the diameter expansion amount of the sealing ring during high-temperature operation, and the width L of all the stress relieving grooves 4 corresponds to the diameter expansion amount of the sealing ring or is slightly smaller than the diameter expansion amount of the sealing ring, so that the sealing ring just closes the stress relieving groove due to thermal expansion during normal operation, and leakage-free sealing is realized.
In the use process, as shown in fig. 2 and 3, the pressure P1 of the cooling gas is applied to the left side of the sealing ring, that is, the inner side of the sealing ring, and the pressure P2 of the high-temperature gas or the pressure P2 of the cooling gas passing through the throttling gas path is applied to the right side of the sealing ring, that is, the outer side of the sealing ring; because the temperature of the inner side of the sealing ring is higher than that of the outer side of the sealing ring, and the pressure of P1 is certainly greater than that of P2, the two arranged sealing surfaces can be more attached to the sealing part under the action of pressure difference, and the sealing efficiency of the sealing ring is effectively improved.
Example two
As shown in fig. 1 to 4, another embodiment of the high-temperature metal sealing ring of the small gas turbine is as follows: the first turbine disk 5 and the second turbine disk 6 are connected in a centering and meshing mode through end face teeth 7; under a high-temperature environment, high-temperature gas generated by the small gas turbine is arranged above the turbine disc I5 and the turbine disc II 6 to push the blades to do work, and a gas path of cooling gas is arranged below the turbine disc I5 and the turbine disc II 6;
when the sealing ring is used, the sealing ring is arranged in the position of the sealing groove between the first turbine disk 5 and the second turbine disk 6, and the sealing matching surface 1 is pressed against the sealing groove after normal installation, so that plane sealing is realized;
after the turbine runs, high-temperature gas generated by the small gas turbine is pushed to do work by the outer side of the meshing position of the first turbine disk 5 and the second turbine disk 6, the air pressure of the outer side of the sealing ring is P2, the inner side of the sealing ring is a cooling gas path, and the air pressure is P1; because the temperature inside and outside the sealing ring is different, the air pressure P1 of the cooling gas inside the sealing ring is higher than the air pressure P2 of the high-temperature gas outside the sealing ring, and pressure difference is formed inside and outside the sealing ring, so that the first matching surface 2 and the second matching surface 3 are extruded and are more attached to the surface of the sealing groove; meanwhile, the metal sealing ring expands and becomes large along with the rise of the temperature, the destressing groove 4 is extruded, and the width L of the destressing groove 4 is narrowed, so that the leakage-free sealing is realized, the problem of stress concentration caused by the high-temperature expansion of the metal sealing ring is solved, and the service life of the sealing ring is effectively prolonged.
Claims (9)
1. A high temperature metal seal ring for a compact gas turbine engine, comprising: the sealing ring, the sealing matching surface (1) and the stress relief groove (4); the sealing matching surface (1) comprises a matching surface I (2) and a matching surface II (3), the matching surface I (2) and the matching surface II (3) are respectively arranged on the upper surface and the lower surface of the sealing ring, and the ring section of the sealing ring between the matching surface I (2) and the matching surface II (3) is in an arc shape which is concave to the center of the sealing ring; the destressing groove (4) is arranged on the inner side of the sealing ring, the depth direction of the destressing groove (4) is perpendicular to the ring shape, and the surface of the deepest position of the destressing groove (4) is in an arc shape.
2. The high temperature metal seal ring for a small gas turbine engine of claim 1, wherein: a plurality of stress relief grooves (4) are formed in the sealing ring, and the number of the stress relief grooves (4) is less than or equal to 4.
3. The high temperature metal seal ring for a compact gas turbine engine of claim 2, wherein: the width L of the stress relief grooves (4) is determined by the diameter expansion amount of the sealing ring in high-temperature work, and the sum of the widths L of all the stress relief grooves (4) and the diameter expansion amount of the sealing ring is less than or equal to the diameter expansion amount of the sealing ring.
4. The high temperature metal seal ring for a small gas turbine engine of claim 1, wherein: the sealing ring is made of high-temperature alloy.
5. The high temperature metal seal ring for a compact gas turbine engine of claim 1, wherein: the surface roughness of the first matching surface (2) and the second matching surface (3) is not more than Ra0.8.
6. The high temperature metal seal ring for a compact gas turbine engine of claim 1, wherein: the free distance between the first matching surface (2) and the second matching surface (3) is 1.005-1.01 times of the width of the sealing groove.
7. The high temperature metal seal ring for a compact gas turbine engine of claim 1, wherein: lead-in chamfers are arranged on the surfaces of the first matching surface (2) and the second matching surface (3).
8. The high temperature metal seal ring for a small gas turbine engine of claim 1, wherein: the sealing ring is manufactured by adopting integrated machining.
9. The high temperature metal seal ring of claim 1 wherein the method of use includes the steps of:
step 1, engaging a turbine disc: the first turbine disk (5) and the second turbine disk (6) are meshed and connected with each other through end face teeth (7);
step 2, installing a sealing ring: installing a sealing ring in a sealing groove between a first turbine disk (5) and a second turbine disk (6), and respectively pressing two sides of the sealing groove by a first matching surface (2) and a second matching surface (3);
step 3, the gas turbine works: the outer side of the sealing ring is provided with a high-temperature gas generated by the small gas turbine to push the blade to do work, the inner side of the sealing ring is provided with a gas path of cooling gas, and the gas pressure P1 of the cooling gas at the inner side is higher than the gas pressure P2 of the high-temperature gas at the outer side, so that the matching surface I (2) and the matching surface II (3) are more attached to the surface of the sealing groove; and the metal sealing ring expands and becomes larger along with the rise of the temperature, and the width L of the stress relief groove (4) becomes narrower.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210854808.0A CN115163311A (en) | 2022-07-18 | 2022-07-18 | High-temperature metal sealing ring of small gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210854808.0A CN115163311A (en) | 2022-07-18 | 2022-07-18 | High-temperature metal sealing ring of small gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115163311A true CN115163311A (en) | 2022-10-11 |
Family
ID=83495827
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210854808.0A Pending CN115163311A (en) | 2022-07-18 | 2022-07-18 | High-temperature metal sealing ring of small gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115163311A (en) |
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2022
- 2022-07-18 CN CN202210854808.0A patent/CN115163311A/en active Pending
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