CN212614893U - High-temperature protection device for stationary blade ring of turbine of gas turbine - Google Patents
High-temperature protection device for stationary blade ring of turbine of gas turbine Download PDFInfo
- Publication number
- CN212614893U CN212614893U CN202021198644.3U CN202021198644U CN212614893U CN 212614893 U CN212614893 U CN 212614893U CN 202021198644 U CN202021198644 U CN 202021198644U CN 212614893 U CN212614893 U CN 212614893U
- Authority
- CN
- China
- Prior art keywords
- pressure plate
- turbine
- chamfer
- stationary blade
- ring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a high-temperature protection device for a turbine stationary blade ring of a gas turbine, which comprises a turbine stationary blade ring outer ring and a turbine stationary blade ring inner ring arranged at the inner side of the turbine stationary blade ring outer ring, wherein a connecting pressure plate groove is arranged at the right angle of the inner side of the turbine stationary blade ring inner ring, a pressure plate chamfer is arranged on the inner wall of the connecting pressure plate groove, a fixed pressure plate is arranged at the inner side of the connecting pressure plate groove, a sealing chamfer is arranged on the surface of one end of the fixed pressure plate, a pressure plate bolt is arranged at the inner side of the sealing chamfer, and a fixed screw hole is arranged at the bottom; the utility model has the advantages that the chamfer is carried out in the connecting pressure plate groove at the right angle part inside the pressure plate bolt and the blade ring, the radius of the chamfer is 5mm, so that the over-concentration of the thermal stress is eliminated; the pressure plate bolt is subjected to chamfering transformation, namely the cross section of the bolt is changed from a rectangle to a trapezoid, so that the chamfering position is completely covered, and the sealing property and the bolt strength of the pressure plate bolt are ensured.
Description
Technical Field
The utility model relates to a gas turbine technical field especially relates to a gas turbine stationary blade ring high temperature protector.
Background
In the maintenance of a gas turbine, the pressure plate of the ring for dividing the turbine stationary blade has damage and meat deficiency phenomena in different degrees, the bolt part of the pressure plate on the inner side of the blade ring has cracks, pitting corrosion and meat deficiency in different degrees, and meanwhile, the whole damaged part is grey white and has obvious high-temperature oxidation characteristics. The blade ring that seriously burns out appears in local position, has obvious elliptical deformation simultaneously along with, the heat shroud ring of fixed turbine quiet leaf and turbine cylinder draw-in groove often appear the jam and unable smooth and easy dismouting from this, and overhauls the result according to nearly 3 nearly turbines of combustion engine, observes that this plastic deformation has obvious aggravation trend, consequently, the urgent need design a combustion engine turbine quiet leaf ring high temperature protector and solves above-mentioned problem.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving the defects existing in the prior art and providing a high-temperature protection device for a turbine stationary blade ring of a combustion engine.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides a combustion engine turbine stationary blade ring high temperature protector, includes turbine stationary blade ring outer lane and sets up at the inboard turbine stationary blade ring inner circle of turbine stationary blade ring outer lane, the inboard right angle department of turbine stationary blade ring inner circle has seted up and has connected the clamp plate groove, the clamp plate chamfer has been seted up to the inner wall of connecting the clamp plate groove, the inboard of connecting the clamp plate groove is provided with solid fixed pressing plate, sealed chamfer has been seted up on solid fixed pressing plate's one end surface, the inboard of sealed chamfer is provided with the clamp plate bolt, solid fixed screw has been seted up to the one end bottom of connecting the clamp plate groove, solid fixed pressing plate is passed to the one end of clamp plate bolt and is closed in solid fixed screw soon, turbine stationary blade ring inner circle, the surface of connecting clamp plate groove, solid fixed.
Furthermore, the chamfer radius of the pressure plate chamfer is five millimeters, and the edge of the fixed pressure plate is matched with the shape of the pressure plate chamfer.
Furthermore, the upper end and the sealing chamfer of the pressure plate bolt are chamfered, the cross section of the upper end of the pressure plate bolt is trapezoidal, and the pressure plate bolt covers the sealing chamfer.
Furthermore, the inboard of turbine stationary blade ring inner circle is provided with the connecting seat, one side of connecting seat is provided with the connecting block, the one end of connecting block is provided with the location arch, the one end of stationary platen is provided with the connector, the connector is installed on the location arch.
Further, the surface of connecting seat is provided with the limiting plate, the spacing groove has been seted up to the inboard surface of connecting block, the limiting plate inserts the spacing inslot.
Furthermore, the surfaces of the inner ring of the turbine stationary blade ring and the fixed pressing plate are polished to be flat, and the upper surface of the pressing plate bolt is located on the lower surface of the nickel-chromium-aluminum-yttrium coating.
The utility model has the advantages that:
1. the utility model has the advantages that the chamfer is carried out in the connecting pressure plate groove at the right angle part inside the pressure plate bolt and the blade ring, the radius of the chamfer is 5mm, so that the over-concentration of the thermal stress is eliminated; the pressure plate bolt is subjected to chamfering transformation, namely the cross section of the bolt is changed from a rectangle to a trapezoid, so that the chamfering position is completely covered, and the sealing property and the bolt strength of the pressure plate bolt are ensured.
2. After the nickel-chromium-aluminum-yttrium coating is transformed, the unit operates stably, the temperature of the turbine DCT is normal, and after the unit operates for one overhaul period, the phenomenon that the bolt of the pressing plate is burnt and damaged frequently in the past is found to disappear completely, the part condition is good, and the improvement effect is very obvious; nickel-chromium-aluminum-yttrium is an important high-temperature oxidation resistant self-bonding spraying material, wherein nickel and aluminum react in an exothermic manner during spraying to form micro-metallurgical bonding between a coating and a matrix, nickel-chromium forms high-temperature oxidation resistant nickel-chromium alloy, and yttrium further improves the performance of the coating.
3. Through the limiting plate and the limiting groove of design, when fixing fixed pressing plate and turbine stationary blade ring inner circle through the connecting block, can be more stable when the block through limiting plate and limiting groove makes the connecting block installation, reduce the vibration that appears when fixed pressing plate is not hard up.
Drawings
FIG. 1 is a schematic structural view of a high temperature protection device for a stationary blade ring of a turbine of a gas turbine according to the present invention;
FIG. 2 is a schematic diagram of a high temperature protection device for a stationary blade ring and a chamfer structure of a stationary blade ring of a gas turbine according to the present invention;
FIG. 3 is a schematic view of a sealing chamfer structure of a high temperature protection device for a stationary blade ring of a combustion engine turbine according to the present invention;
fig. 4 is the utility model provides a fixed blade ring high temperature protection device's of combustion engine turbine limiting plate and spacing groove structural schematic.
In the figure: the turbine stator blade ring comprises a turbine stator blade ring outer ring 1, a turbine stator blade ring inner ring 2, a connecting pressure plate groove 3, a fixing pressure plate 4, a connecting block 5, a connecting seat 6, a pressure plate bolt 7, a fixing screw hole 8, a connecting head 9, a sealing chamfer 10, a limiting plate 11, a limiting groove 12, a positioning bulge 13, a nickel-chromium-aluminum-yttrium coating 14 and a pressure plate chamfer 15.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
It will be understood that when an element is referred to as being "secured to" another element, it can be directly on the other element or intervening elements may also be present. When a component is referred to as being "connected" to another component, it can be directly connected to the other component or intervening components may also be present. When a component is referred to as being "disposed on" another component, it can be directly on the other component or intervening components may also be present. The terms "vertical," "horizontal," "left," "right," and the like as used herein are for illustrative purposes only.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The terminology used in the description of the invention herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
Referring to fig. 1 to 4, a high temperature protection device for a turbine stationary blade ring of a combustion engine comprises an outer ring 1 of the turbine stationary blade ring and an inner ring 2 of the turbine stationary blade ring arranged on the inner side of the outer ring 1 of the turbine stationary blade ring, a connecting pressure plate groove 3 is arranged at the right angle of the inner side of the inner ring 2 of the turbine stationary blade ring, a pressure plate chamfer 15 is arranged on the inner wall of the connecting pressure plate groove 3, a fixed pressure plate 4 is arranged on the inner side of the connecting pressure plate groove 3, a sealing chamfer 10 is arranged on the surface of one end of the fixed pressure plate 4, a pressure plate bolt 7 is arranged on the inner side of the sealing chamfer 10, a fixed screw hole 8 is arranged at the bottom of one end of the connecting pressure plate groove 3, one end of the pressure plate bolt 7 passes through the fixed pressure plate 4 to be screwed in the fixed screw hole 8, and nichrome, the excessive concentration of the thermal stress is eliminated by turning a pressure plate chamfer 15 at the joint of the connecting pressure plate groove 3 and the fixed pressure plate 4.
Further, the chamfer radius of the pressure plate chamfer 15 is five millimeters, and the edge of the fixed pressure plate 4 is matched with the shape of the pressure plate chamfer 15.
Further, the upper end of the pressing plate bolt 7 and the sealing chamfer 10 are chamfered, the section of the upper end of the pressing plate bolt 7 is trapezoidal, the pressing plate bolt 7 covers the sealing chamfer 10, and the pressing plate bolt 7 is conveniently and stably sealed and installed in the sealing chamfer 10, so that the fixed pressing plate 4 is fixed.
Further, the inner side of the turbine stationary blade ring inner ring 2 is provided with a connecting seat 6, one side of the connecting seat 6 is provided with a connecting block 5, one end of the connecting block 5 is provided with a positioning protrusion 13, one end of the fixed pressing plate 4 is provided with a connecting head 9, the connecting head 9 is installed on the positioning protrusion 13, and the connecting block 5 is connected more stably through the fixed pressing plate 4 when being installed.
Further, the surface of connecting seat 6 is provided with limiting plate 11, and limiting groove 12 has been seted up to the inboard surface of connecting block 5, and limiting plate 11 inserts limiting groove 12 in, and the block through limiting plate 11 and limiting groove 12 makes connecting block 5 install stably.
Furthermore, the surfaces of the turbine stationary blade ring inner ring 2 and the fixed pressing plate 4 are polished to be flat, and the upper surface of the pressing plate bolt 7 is located on the lower surface of the nickel-chromium-aluminum-yttrium coating 14, so that the nickel-chromium-aluminum-yttrium coating 14 is better prevented from being concave and convex during spraying.
The utility model discloses a spraying nickel chromium aluminium yttrium coating 14 adopts the spraying nickel chromium aluminium yttrium (NiCrAlY, Ni ≧ 66%, Cr 21% ~ 23%, Al 9% ~ 11%, Y0.8% ~ 1.2%) spraying process during the spraying, and nickel chromium aluminium yttrium is important high temperature oxidation resistance self bonding spraying material, and wherein nickel and aluminium exothermal reaction when the spraying makes coating and base member form little metallurgical bonding, and nickel chromium forms high temperature oxidation resistance's nickel chromium alloy, and yttrium then further improves coating performance. The bonding strength of nickel, chromium, aluminum and yttrium is not less than 50MPa, the macroscopic hardness HRb is 50-80, the porosity is not more than 1%, and the alloy resists corrosive gas and high-temperature oxidation (can reach 1120 ℃).
And the spraying process is adopted, and the spraying process mainly considers that the surface of the sprayed product is rough, is not as fine and precise as plasma spraying, but is easier to dissipate heat, and is more suitable for high-temperature severe working areas such as turbine smoke and the like.
The spraying of nickel chromium aluminum yttrium is a very mature coating process, and the melted nickel chromium aluminum yttrium is covered on a blade ring segmentation ring area by utilizing heat energy, so that the blade ring body is well protected from heat.
The working principle is as follows: when using, go out clamp plate chamfer 15 through turning to connecting clamp plate groove 3 and fixed pressing plate 4, turn out sealed chamfer 10 on the fixed pressing plate 4, too concentrated with this elimination its thermal stress, through nichrome aluminium yttrium coating 14 spraying after, the unit operates steadily, turbine DCT temperature is normal, and after an overhaul cycle of operation, the clamp plate bolt that discovery frequently appears in the past burns out the phenomenon and disappears completely, the part situation is good, it is very obvious to improve the effect, and limiting plate 11 and spacing groove 12 through the design, when fixing fixed pressing plate 4 and turbine stationary blade ring inner circle 2 through connecting block 5, it is more stable when the block that can make connecting block 5 install through limiting plate 11 and spacing groove 12.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (6)
1. The utility model provides a combustion engine turbine quiet leaf ring high temperature protector, includes turbine quiet leaf ring outer lane (1) and sets up at inboard turbine quiet leaf ring inner circle (2) of turbine quiet leaf ring outer lane (1), a serial communication port, connection clamp plate groove (3) have been seted up to the inboard right angle department of turbine quiet leaf ring inner circle (2), clamp plate chamfer (15) have been seted up to the inner wall of connecting clamp plate groove (3), the inboard of connecting clamp plate groove (3) is provided with fixed clamp plate (4), sealed chamfer (10) have been seted up on the one end surface of fixed clamp plate (4), the inboard of sealed chamfer (10) is provided with clamp plate bolt (7), fixed screw (8) have been seted up to the one end bottom of connecting clamp plate groove (3), the one end of clamp plate bolt (7) is passed fixed clamp plate (4) and is closed in fixed screw (8) soon, turbine quiet leaf ring inner circle (2) quiet leaf ring, The surfaces of the connecting pressing plate groove (3), the fixed pressing plate (4) and the pressing plate chamfer angle (15) are all provided with nickel-chromium-aluminum-yttrium coatings (14).
2. The high-temperature protection device for the stationary blade ring of a combustion engine turbine as claimed in claim 1, characterized in that the chamfer radius of the pressure plate chamfer (15) is five millimeters, and the edge of the stationary pressure plate (4) matches the shape of the pressure plate chamfer (15).
3. The high-temperature protection device for the turbine stationary blade ring of the combustion engine as claimed in claim 1, wherein the upper end of the pressure plate bolt (7) and the sealing chamfer (10) are chamfered, the cross-sectional shape of the upper end of the pressure plate bolt (7) is trapezoidal, and the pressure plate bolt (7) is covered in the sealing chamfer (10).
4. The high-temperature protection device for the turbine stationary blade ring of the combustion engine according to claim 1, wherein the inner side of the inner ring (2) of the turbine stationary blade ring is provided with a connecting seat (6), one side of the connecting seat (6) is provided with a connecting block (5), one end of the connecting block (5) is provided with a positioning protrusion (13), one end of the fixed pressing plate (4) is provided with a connecting head (9), and the connecting head (9) is installed on the positioning protrusion (13).
5. The high-temperature protection device for the turbine stationary blade ring of the combustion engine according to claim 4, wherein a limiting plate (11) is arranged on the surface of the connecting seat (6), a limiting groove (12) is formed on the inner side surface of the connecting block (5), and the limiting plate (11) is inserted into the limiting groove (12).
6. The high-temperature protection device for the turbine stationary blade ring of the combustion engine as claimed in claim 1, wherein the surfaces of the inner ring (2) of the turbine stationary blade ring and the fixed pressure plate (4) are polished flat, and the upper surface of the pressure plate bolt (7) is located on the lower surface of the nickel chromium aluminum yttrium coating (14).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021198644.3U CN212614893U (en) | 2020-06-24 | 2020-06-24 | High-temperature protection device for stationary blade ring of turbine of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021198644.3U CN212614893U (en) | 2020-06-24 | 2020-06-24 | High-temperature protection device for stationary blade ring of turbine of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212614893U true CN212614893U (en) | 2021-02-26 |
Family
ID=74743144
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021198644.3U Active CN212614893U (en) | 2020-06-24 | 2020-06-24 | High-temperature protection device for stationary blade ring of turbine of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212614893U (en) |
-
2020
- 2020-06-24 CN CN202021198644.3U patent/CN212614893U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN212614893U (en) | High-temperature protection device for stationary blade ring of turbine of gas turbine | |
| CN201531326U (en) | Engine cylinder head gasket | |
| CN112901278B (en) | Turbine blade adopting buckle fixed ceramic armor | |
| CN209781056U (en) | High-efficient reliable sealed natural gas cylinder head structure of cooling | |
| CN204082362U (en) | New ceramics armouring internal combustion engine | |
| CN111102095B (en) | Low heat dissipation composite structure piston | |
| CN114109519A (en) | Guide blade based on metal base band ceramic mosaic block | |
| CN210948927U (en) | Novel sealing piston ring | |
| CN110936201B (en) | Tool for machining precision-forged blade and using method thereof | |
| CN209818178U (en) | Heat insulation piston | |
| CN207004671U (en) | Diesel engine and its Rocker arm chamber cap component | |
| CN113638777A (en) | Turbine outer ring clamp, cooling structure of turbine outer ring, turbine and engine | |
| CN208502860U (en) | A kind of camshaft mounting structure of motorcycle upper camshaft formula engine | |
| CN211422784U (en) | Novel cylinder cover exhaust passage structure | |
| CN210164512U (en) | Integrated form valve seat structure | |
| CN206439120U (en) | Engine and its cylinder gasket | |
| CN218407604U (en) | Easy-to-cool anti-cracking diesel engine body for generator set | |
| CN217270454U (en) | Light-weight cushion block for oil cooler of heavy gasoline and diesel engine | |
| CN211777617U (en) | Medium-low pressure cylinder steel casting of cogeneration unit | |
| CN208816218U (en) | A kind of exhaust manifold | |
| CN214944443U (en) | Turbine stator blade ring steel casting of combustion engine | |
| CN215520978U (en) | Gas compressor stator blade retaining ring steel casting of gas turbine | |
| CN214787732U (en) | 350mm cylinder diameter medium-speed high-power piston | |
| CN210919162U (en) | Novel high temperature resistant nozzle cascade subassembly | |
| CN202596918U (en) | An undercut-profile easily-recyclable cylinder gasket provided with a covered edge |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |