CN107366558B - Radial rim sealing structure with stator tail edge opening pumping and ejecting function - Google Patents
Radial rim sealing structure with stator tail edge opening pumping and ejecting function Download PDFInfo
- Publication number
- CN107366558B CN107366558B CN201710689987.6A CN201710689987A CN107366558B CN 107366558 B CN107366558 B CN 107366558B CN 201710689987 A CN201710689987 A CN 201710689987A CN 107366558 B CN107366558 B CN 107366558B
- Authority
- CN
- China
- Prior art keywords
- stator
- tail edge
- hole
- pumping hole
- pumping
- 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
Classifications
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
Abstract
The invention discloses a radial rim sealing structure with a stator tail edge opening hole pumping hole. A three-dimensional stator tail edge pumping hole is formed by the stator tail edge and the inner wall surface of the rim sealing static part. The stator tail edge pumping holes are distributed in an inclined mode along the circumferential direction and are of smooth transition hook-shaped structures along the radial direction, low-energy fluid which is close to the hub in the stator tail edge action area is sprayed out from the inner wall face of the sealing static portion of the wheel rim through the stator tail edge pumping holes, flowing resistance of the intrusion flow at the sealing gap is effectively increased, the gas intrusion degree is further reduced, and heat transfer stability of the turbine disc is improved. Meanwhile, low-energy gas at the tail edge of the stator is sucked and secondarily utilized, so that the energy utilization rate of the turbine and the efficiency of the whole turbine are improved.
Description
Technical Field
The invention relates to the technical field of gas turbine turbines, in particular to a radial rim sealing structure with a stator tail edge opening hole for extraction and ejection.
Background
An annular cavity is formed between a low-pressure turbine rotating disc and a static part of the gas turbine and is called as a turbine disc cavity, and the invasion of gas in the turbine disc cavity refers to that when the turbine disc rotates, air in the disc cavity is continuously pumped out by a friction pump effect to reduce the pressure in the cavity, and under the action of the friction pump effect, when the pumped-out flow is greater than the supply flow of cold air, the invasion of gas at the wheel edge of the turbine disc can occur, namely main gas enters the disc cavity; the mutual interference of the transfer stators in the main flow passage causes the circumferential pressure fluctuation of the main fuel gas and also forms the invasion phenomenon of the tight sealing position. Researches show that the gas invasion phenomenon is an important factor causing the overheating failure of the turbine disc, the invasion phenomenon is generated, the cooling effect of the disc cavity is damaged, the safe and reliable operation of the whole machine is damaged, and the loss of the efficiency of the whole machine is caused at the same time. At present, the project is mainly solved by measures of introducing low-temperature cooling airflow from a compressor stage to cool a turbine disc, installing a rim seal with an advanced structure and the like.
The rim is hermetically installed at the edge of the chamber of the rotating-stationary disk, and the invasion of gas can be suppressed by increasing the flow resistance of the high-temperature invasion flow invading the turbine disk, thereby having a significant influence on the safety performance of the turbine disk. Research shows that the degree of gas invasion can be obviously reduced by increasing the flow resistance of the invasion flow on the disc surface.
Patent CN105134306A discloses "a radial rim sealing structure with damping holes and guide vanes", which can effectively reduce the degree of gas intrusion by providing honeycomb-type damping holes and guide vanes of tapered channels to increase the flow resistance to the intrusion flow. Patent CN105626157A discloses a multiple rim seal structure including self-adaptation fumarole, through just having opened the self-adaptation fumarole with quiet leaf side seal tooth top end to moving impeller hub flange board downside edge, has increased the resistance that main gas got into the dish chamber, has improved obturating performance and turbine efficiency. Therefore, the rim sealing structure capable of increasing the flow resistance of the intrusion flow has important engineering application value for improving the heat transfer stability of the turbine disc and improving the economy of the whole machine.
Disclosure of Invention
In order to avoid the defects in the prior art, the invention provides a radial rim sealing structure with a stator tail edge opening hole for pumping, which can effectively increase the flow resistance of an invasion flow at a sealing gap, reduce the invasion degree of fuel gas, reduce the temperature of a turbine disc and improve the heat transfer stability of the turbine disc; meanwhile, low-energy gas at the tail edge of the stator is pumped and secondarily utilized to be sprayed out of the wall surface of the cavity, so that the energy utilization rate of the turbine and the efficiency of the whole turbine are improved.
The invention solves the technical problem by adopting the technical scheme that the device comprises a stator tail edge pumping hole, wherein the stator tail edge pumping hole is positioned inside a static part of a rim sealing structure;
the inlet of the stator tail edge pumping hole is a circular hole, and the distance between the inlet of the stator tail edge pumping hole and the stator blade tail edge is 2-4 times of the diameter of the circular hole;
the outlet of the stator tail edge pumping hole is a circular hole, the outlet of the stator tail edge pumping hole is positioned on the inclined wall surface of the lower half section of the static part of the rim sealing structure, the position on the inclined wall surface is 1/4-1/3 away from the left end of the inclined wall surface, and the outlet section is vertical to the inclined wall surface;
the diameter of an outlet of the stator tail edge pumping hole is the same as that of an inlet of the stator tail edge pumping hole, and a contraction channel structure is adopted by an outlet circular hole and an inlet circular hole section of the stator tail edge pumping hole; the stator tail edge pumping holes are distributed in an inclined manner along the circumferential direction, and the inclined angle corresponds to the inclined angle of the stator pressure surface outlet or is smaller than the inclined angle of the stator pressure surface outlet; the pumping hole at the tail edge of the stator is in a smooth transition hook-shaped structure along the radial direction.
The central axis of the stator tail edge pumping hole and the tail edge arc center of the stator blade are positioned on the same straight line.
The number of the pumping holes at the tail edge of the stator is the same as that of the stator blades.
And the diameter of an inlet of the stator tail edge extraction hole is determined according to the flow rate required to be extracted.
Advantageous effects
The invention provides a radial rim sealing structure with a stator tail edge opening hole pumping hole. A stator tail edge pumping hole in three-dimensional distribution is constructed on the inner wall surface of the stator tail edge and the flange sealing static part. The stator trailing edge pumping holes are distributed in an inclined mode along the circumferential direction and are of smooth transition hook-shaped structures along the radial direction, low-energy fluid which is close to a hub in a stator trailing edge action area is ejected out of the inner wall face of a sealed static part of a rim through the stator trailing edge pumping holes, flowing resistance of an intrusion flow at a sealing gap is effectively increased, the gas intrusion degree is further reduced, the temperature of a turbine disc is reduced, and the heat transfer stability of the turbine disc is improved. Meanwhile, low-energy gas at the tail edge of the stator is sucked and secondarily utilized, so that the energy utilization rate of the turbine is improved, and the heat transfer stability of the turbine disc and the efficiency of the whole machine are improved.
Drawings
The present invention will be described in further detail with reference to the drawings and embodiments, wherein the radial rim seal structure with stator trailing edge opening pumping is provided.
FIG. 1 is a schematic cross-sectional view of a turbine stage rim seal and stator trailing edge extraction hole configuration of the present invention.
Fig. 2 is a top view of a stator trailing edge extraction aperture arrangement.
In the drawings
1. Rotor and stator disc cavity 2, rim sealing structure 3, stator tail edge extraction hole 4, stator blade 5, rotor blade 6, stator disc 7 and rotor disc
Detailed Description
The embodiment is a radial rim seal structure with stator trailing edge opening extraction.
Referring to fig. 1 and 2, in the present embodiment, the radial rim sealing structure with the stator trailing edge opening hole is provided for pumping, the stator trailing edge pumping hole 3 is located inside the stationary part of the rim sealing structure 2, the inlet of the stator trailing edge pumping hole 3 is located in the stator trailing edge acting region, and the outlet of the stator trailing edge pumping hole 3 is located on the wall surface of the stationary part of the rim sealing structure 2.
The inlet of the stator trailing edge pumping hole 3 is a circular hole, the number of the circular holes is the same as that of the stator blades 4, or the circular holes are taken as the common divisor of the number of the stator blades 4 and the number of the rotor blades 5; the diameter of the circular hole is the diameter corresponding to the arc of the tail edge of the stator blade 4; the inlet of the stator tail edge pumping hole is located in the tail edge action area of the stator blade 4, and the distance from the tail edge is 2-4 times of the diameter of the circular hole. The inlet section of the stator trailing edge extraction hole 3 adopts a contracted channel structure for the convenience of extracting the main flow, namely, the inlet diameter is larger for capturing the airflow, and the channel is gradually reduced to compress the airflow. Because the airflow at the tail edge of the stator mainly takes the tangential velocity as the main part, the axial velocity is relatively reduced, and the radial velocity is almost zero, the circular hole inlet of the pumping hole 3 at the tail edge of the stator can be an elliptical inlet, and the length ratio of the long axis to the short axis is the ratio of the circumferential velocity to the axial velocity.
The outlet of the stator tail edge pumping hole 3 is a circular hole, and the number of the circular holes is the same as that of the inlet circular holes. The diameter of the circular hole at the outlet of the stator tail edge pumping hole 3 is the same as that of the circular hole at the inlet, and the outlet section is processed into a contraction channel so as to accelerate the ejection of air flow and generate stronger blocking effect. The outlet of the stator trailing edge pumping hole 3 is positioned on the inclined wall surface of the lower half section of the static part of the rim sealing structure 2, and the position on the inclined wall surface is selected to be the length from the left end of the inclined wall surface, which is 1/4-1/3 of the length of the inclined wall surface; the outlet section is perpendicular to the inclined wall. The angle of inclination is determined according to the effect of the desired spray.
The stator tail edge pumping hole 3 is positioned in the static part of the rim sealing structure 2 to form a three-dimensional distributed hole structure; the stator trailing edge pumping holes 3 are distributed in an inclined mode along the circumferential direction, and the inclined angle corresponds to the inclined angle of the stator pressure surface outlet or is smaller than the inclined angle of the stator pressure surface outlet. In order to ensure that the stator tail edge pumping hole is respectively kept vertical to the wall surface of the stator hub and the inclined wall surface of the lower half section of the stationary part of the rim sealing structure in the radial direction and ensure that the hole structure is in smooth transition so as to reduce the loss of a molded surface, the stator tail edge pumping hole is in a hook-shaped structure in smooth transition in the radial direction. Because the temperature of the main flow gas of the high-pressure turbine is higher, the extraction holes 3 at the tail edge of the stator can be ablated, and the high-pressure turbine is selected to be used on the low-pressure turbine with lower temperature.
In the embodiment, a three-dimensional circular hole channel is formed by the tail edge of the stator blade 4 and the inner wall surface of the static part of the rim sealing structure 2, namely the stator tail edge pumping hole 3, so that low-energy fluid in a stator tail edge action area, which is close to the hub, is ejected out of the inner wall surface of the rim sealing static part through the stator tail edge pumping hole 3, the flow resistance of the intrusion flow at the sealing gap is effectively increased, and the intrusion degree of fuel gas is further reduced. Meanwhile, low-energy gas at the tail edge of the stator blade 4 is sucked and secondarily utilized, so that the energy utilization rate of the turbine is improved, and the purposes of improving the heat transfer stability of the turbine disc and improving the economy of the whole machine are achieved.
Claims (4)
1. A radial rim sealing structure with a stator tail edge opening hole pumping hole is characterized by comprising a stator tail edge pumping hole, wherein the stator tail edge pumping hole is positioned in the static part of the rim sealing structure;
the inlet of the stator tail edge pumping hole is a circular hole, and the distance between the inlet of the stator tail edge pumping hole and the stator blade tail edge is 2-4 times of the diameter of the circular hole;
the outlet of the stator tail edge pumping hole is a circular hole, the outlet of the stator tail edge pumping hole is positioned on the inclined wall surface of the lower half section of the static part of the rim sealing structure, the position on the inclined wall surface is 1/4-1/3 away from the left end of the inclined wall surface, and the outlet section is vertical to the inclined wall surface;
the diameter of an outlet of the stator tail edge pumping hole is the same as that of an inlet of the stator tail edge pumping hole, and an outlet section of the stator tail edge pumping hole adopts a contraction channel structure; the stator tail edge pumping holes are distributed in an inclined manner along the circumferential direction, and the inclined angle corresponds to the inclined angle of the stator pressure surface outlet or is smaller than the inclined angle of the stator pressure surface outlet; the pumping hole at the tail edge of the stator is in a smooth transition hook-shaped structure along the radial direction.
2. The radial rim seal structure with stator trailing edge perforated extraction of claim 1, wherein the central axis of the stator trailing edge perforated extraction hole is aligned with the arc center of the trailing edge of the stator blade.
3. A radial rim seal with stator trailing edge perforated drainage as claimed in claim 1 wherein the number of stator trailing edge perforated drainage holes is the same as the number of stator vanes.
4. The radial rim seal with stator trailing edge perforated extraction of claim 1, wherein the inlet diameter of the stator trailing edge extraction hole is determined by the flow rate to be extracted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710689987.6A CN107366558B (en) | 2017-08-14 | 2017-08-14 | Radial rim sealing structure with stator tail edge opening pumping and ejecting function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710689987.6A CN107366558B (en) | 2017-08-14 | 2017-08-14 | Radial rim sealing structure with stator tail edge opening pumping and ejecting function |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107366558A CN107366558A (en) | 2017-11-21 |
| CN107366558B true CN107366558B (en) | 2020-08-07 |
Family
ID=60309994
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710689987.6A Active CN107366558B (en) | 2017-08-14 | 2017-08-14 | Radial rim sealing structure with stator tail edge opening pumping and ejecting function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107366558B (en) |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3291447A (en) * | 1965-02-15 | 1966-12-13 | Gen Electric | Steam turbine rotor cooling |
| DE102008011746A1 (en) * | 2008-02-28 | 2009-09-03 | Mtu Aero Engines Gmbh | Device and method for diverting a leakage current |
| JP2017057838A (en) * | 2015-09-18 | 2017-03-23 | 株式会社東芝 | Gas turbine cooling structure and gas turbine |
-
2017
- 2017-08-14 CN CN201710689987.6A patent/CN107366558B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN107366558A (en) | 2017-11-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP5060737B2 (en) | Centrifugal pump and its impeller | |
| CN101769203B (en) | Methods, systems and/or apparatus relating to inducers for turbine engines | |
| US20160281732A1 (en) | Impeller with offset splitter blades | |
| US9810226B2 (en) | Axial compressor | |
| JP6159151B2 (en) | Turbine blade | |
| US20130142651A1 (en) | Turbine impeller comprising blade with squealer tip | |
| CN105134306B (en) | Radial rim sealing structure with damping holes and flow guide blades | |
| CN111720175B (en) | Impeller machinery movable vane top seal structure | |
| JP2016125486A (en) | Gas turbine sealing | |
| JP2016538469A (en) | Rotor outflow assembly for improved pressure recovery | |
| EP2480793A1 (en) | Diffuser | |
| CN107387170A (en) | A kind of supercharging rotor disc structure of prewhirling for wheel rim sealing | |
| US8480351B2 (en) | Compressor unit | |
| US9638211B2 (en) | Scroll tongue part and rotary machine including the same | |
| CN212671868U (en) | Impeller machinery movable vane top seal structure | |
| JP2014152637A (en) | Centrifugal compressor | |
| CN107366558B (en) | Radial rim sealing structure with stator tail edge opening pumping and ejecting function | |
| WO2016160393A1 (en) | Diffuser having multiple rows of diffuser vanes with different solidity | |
| JP2018135836A (en) | Centrifugal compressor | |
| JPH09317696A (en) | Stator blade structure of axial flow compressor | |
| CN211819519U (en) | Turbine static disk, turbine and gas turbine | |
| CN212389569U (en) | Sealing mechanism, axial flow compressor and gas turbine | |
| JP6265000B2 (en) | Centrifugal compressor | |
| US10174766B2 (en) | Diffuser for a forward-swept tangential flow compressor | |
| JP6402569B2 (en) | Centrifugal compressor and centrifugal compressor design method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |