CN115680789A - Guide vane lower edge plate mouth-biting sealing structure - Google Patents
Guide vane lower edge plate mouth-biting sealing structure Download PDFInfo
- Publication number
- CN115680789A CN115680789A CN202211706483.8A CN202211706483A CN115680789A CN 115680789 A CN115680789 A CN 115680789A CN 202211706483 A CN202211706483 A CN 202211706483A CN 115680789 A CN115680789 A CN 115680789A
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- Prior art keywords
- guide vane
- inner ring
- front half
- sealing
- labyrinth
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- 238000007789 sealing Methods 0.000 title claims abstract description 40
- 210000003141 lower extremity Anatomy 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract 1
- 238000009434 installation Methods 0.000 description 4
- 208000002193 Pain Diseases 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 206010031009 Oral pain Diseases 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004826 seaming Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to the aeroengine field, in particular to structure of obturating is chewed to stator lower limb board. The method comprises the following steps: the high vortex rear baffle, the low guide vane and the front half of the guide vane inner ring. The high-vortex rear baffle is provided with a high-vortex rear baffle sealing tooth and a labyrinth mounting edge which extend backwards along the axial direction, and the end part of the labyrinth mounting edge is provided with a labyrinth which extends outwards along the radial direction; the low guide blade is provided with a guide blade lower edge plate, a low guide blade sealing tooth extending forwards along the axial direction is arranged on the guide blade lower edge plate, a mouthpiece sealing cavity is formed between the low guide blade sealing tooth and the guide blade lower edge plate, the mouthpiece sealing cavity realizes primary sealing by accommodating a high vortex rear baffle sealing tooth, and an inner ring front half mounting plate extending inwards along the radial direction is arranged on the low guide blade sealing tooth; the front half of the guide vane inner ring is arranged on the front half mounting plate of the inner ring, the front half of the guide vane inner ring is provided with the front half honeycomb of the guide vane inner ring, and the front half honeycomb of the guide vane inner ring is matched with the comb teeth to realize secondary sealing. The risk that this application can reduce the inner ring overtemperature promotes the reliability.
Description
Technical Field
The application belongs to the field of aeroengine blades, and particularly relates to a structure for sealing a lower edge plate nozzle of a guide vane.
Background
The front half material of the guide vane inner ring is high-temperature alloy, and the temperature bearing capacity of the material is about 800 ℃. At present, the sealing labyrinth structure of the lower guide vane edge plate is adopted to realize the sealing of the main channel gas, the structure has the risk of overtemperature of the mounting edge of the inner guide vane ring due to the fact that the main channel gas enters the matching position of the front mounting edge of the inner guide vane ring and the lower guide vane edge plate, and once the main channel gas enters the matching position of the front mounting edge of the inner guide vane ring and the guide vane, the mounting edge of the inner guide vane ring can be damaged, and the service life of the inner guide vane ring is shortened.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The utility model aims at providing a structure of obturating is stung to stator lower limb board to solve at least one problem that exists among the prior art.
The technical scheme of the application is as follows:
a structure is obturated to stator lower flange board seaming, includes:
the high-vortex rear baffle is arranged on the high-pressure turbine disc, a high-vortex rear baffle sealing tooth and a labyrinth mounting edge which extend backwards along the axial direction are arranged on the high-vortex rear baffle, and a labyrinth extending outwards along the radial direction is arranged at the end part of the labyrinth mounting edge;
the low guide blade is provided with a guide blade lower edge plate, a low guide blade sealing tooth extending forwards along the axial direction is arranged on the guide blade lower edge plate, a mouthpiece sealing cavity is formed between the low guide blade sealing tooth and the guide blade lower edge plate, the mouthpiece sealing cavity achieves primary sealing by accommodating the high vortex rear baffle sealing tooth, and an inner ring front half mounting plate extending inwards along the radial direction is arranged on the low guide blade sealing tooth;
the first half of stator inner ring, the first half of stator inner ring is installed on the first half mounting panel of inner ring, the first half of stator inner ring is provided with the first half honeycomb of stator inner ring, the first half honeycomb of stator inner ring with the labyrinth cooperation realizes the second grade and seals.
In at least one embodiment of this application, be provided with joint portion on the high vortex backplate, be provided with the draw-in groove of adaptation on the high pressure turbine dish, the joint portion cooperation snap ring of high vortex backplate with the high pressure turbine dish joint.
In at least one embodiment of the present application, the labyrinth comprises at least two tooth structures.
In at least one embodiment of this application, it has stator top flange to hang down the blade, be provided with preceding couple and stator back installation limit on the stator top flange respectively, the stator top flange passes through preceding couple and stator back installation limit cooperation is installed on the low pressure machine casket.
In at least one embodiment of this application, set up inner ring front half mounting edge on the stator inner ring front half, inner ring front half mounting edge through the pin with inner ring front half mounting panel is connected.
The invention has at least the following beneficial technical effects:
the utility model provides a structure of obturating is chewed to stator bottom flange, with the first half installation edge turn-ups cancellation of stator inner ring, increase a low guide blade tooth of obturating on stator bottom flange, through the structure of obturating of the stinging mouth that stator bottom flange and high whirlpool backplate formed, make the inner ring keep away from the runner, reduced the risk of inner ring overtemperature, promoted the reliability of low pressure turbine.
Drawings
FIG. 1 is a schematic view of a vane lower edge plate mouthpiece seal configuration of an embodiment of the present application;
FIG. 2 is a schematic view of a high vortex tailgate mounting arrangement according to an embodiment of the present application;
FIG. 3 is a schematic view of a vane lower edge plate according to an embodiment of the present application.
Wherein:
1-high vortex blade; 2-high vortex back baffle seal teeth; 3-high vortex tailgate; 4-a high pressure turbine disk; 5-a low-voltage casing; 6-low guide vane; 7-low guide vane sealing teeth; 8-front half of the guide vane inner ring.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described are some, but not all embodiments of the disclosure. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "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 used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 3.
The application provides a stator lower flange board is difficult to articulate and is sealed structure includes: a high vortex backplate 3, a low guide vane 6 and a guide vane inner ring front half 8.
Specifically, as shown in fig. 1, the high vortex blade 1 is connected to the high pressure turbine disc 4 through a disc tenon structure, a clamping portion is arranged on the radial inner side of the high vortex backplate 3, a clamping groove matched with the high pressure turbine disc 4 is arranged on the high pressure turbine disc 4, the clamping portion of the high vortex backplate 3 is clamped with the high pressure turbine disc 4 in a matched manner (see fig. 2), a high vortex backplate sealing tooth 2 extending backwards along the axial direction and a labyrinth mounting edge are arranged on the high vortex backplate 3, a labyrinth extending outwards along the radial direction is arranged at the end of the labyrinth mounting edge, and the labyrinth comprises at least two tooth structures.
The low guide vane 6 is provided with a guide vane upper edge plate, a front hook and a guide vane rear mounting edge are respectively arranged on the guide vane upper edge plate, the guide vane upper edge plate is hooked with a hook on the front side of the low-pressure casing 5 through the front hook and is connected with a mounting structure on the rear side of the low-pressure casing 5 through a guide vane rear mounting edge matching pin; the low guide blade 6 is also provided with a guide blade lower edge plate, referring to fig. 3, a low guide blade sealing tooth 7 extending forwards along the axial direction is arranged on the guide blade lower edge plate, a mouthpiece sealing cavity is formed between the low guide blade sealing tooth 7 and the guide blade lower edge plate, the mouthpiece sealing cavity realizes one-stage sealing by accommodating the high vortex rear baffle sealing tooth 2, and an inner ring front half mounting plate extending inwards along the radial direction is arranged on the low guide blade sealing tooth 7.
The guide vane inner ring front half 8 is provided with an inner ring front half mounting edge, the inner ring front half mounting edge is connected with the inner ring front half mounting plate through a pin, the guide vane inner ring front half 8 is provided with a guide vane inner ring front half honeycomb, and the guide vane inner ring front half honeycomb is matched with the labyrinth to realize secondary sealing.
The utility model provides a structure of obturating of stator lower limb mouth of stinging, through the structure of obturating of mouth of stinging and the structure of obturating of labyrinth realize the two-stage and obturate, dish chamber air conditioning forms the obturate to the main entrance gas through the structure of obturating of mouth of stinging, prevents that the main entrance gas from flowing backward.
The utility model provides a structure of obturating is stung to stator lower limb board, it is single crystal material to hang down guide vane 6, its temperature-bearing ability is about 1100 ℃, be higher than the stator inner ring, consequently with the first half installation edge turn-ups cancellation of stator inner ring, it leads blade tooth 7 to increase one low on stator lower limb board, through the structure of obturating of the stung of stator lower limb board and high whirlpool backplate formation, make the inner ring keep away from the runner, the risk that the inner ring overtemperature has been reduced, the reliability of low pressure turbine has been promoted.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. The utility model provides a structure of obturating is chewed to stator lower flange board which characterized in that includes:
the high-vortex rear baffle (3) is mounted on the high-pressure turbine disc (4), a high-vortex rear baffle sealing tooth (2) extending backwards along the axial direction and a labyrinth mounting edge are arranged on the high-vortex rear baffle (3), and a labyrinth extending outwards along the radial direction is arranged at the end part of the labyrinth mounting edge;
the low guide vane (6) is provided with a guide vane lower edge plate, a low guide vane sealing tooth (7) extending forwards along the axial direction is arranged on the guide vane lower edge plate, a mouthpiece sealing cavity is formed between the low guide vane sealing tooth (7) and the guide vane lower edge plate, the mouthpiece sealing cavity realizes primary sealing by accommodating the high vortex rear baffle sealing tooth (2), and an inner ring front half mounting plate extending inwards along the radial direction is arranged on the low guide vane sealing tooth (7);
guide vane inner ring first half (8), guide vane inner ring first half (8) are installed on the inner ring first half mounting panel, be provided with guide vane inner ring first half honeycomb on guide vane inner ring first half (8), guide vane inner ring first half honeycomb with the labyrinth cooperation realizes the second grade and seals.
2. The structure of claim 1, characterized in that the high vortex backplate (3) is provided with a clamping portion, the high pressure turbine disc (4) is provided with a clamping groove, and the clamping portion of the high vortex backplate (3) is matched with a clamping ring to be clamped with the high pressure turbine disc (4).
3. The guide vane lower edge plate mouthpiece seal structure of claim 1, wherein the labyrinth comprises at least two tooth structures.
4. The structure of claim 1, characterized in that the lower guide vane (6) has an upper guide vane edge, the upper guide vane edge is provided with a front hook and a rear guide vane mounting edge, and the upper guide vane edge is mounted on the low-pressure casing (5) through the front hook and the rear guide vane mounting edge.
5. The lower edge plate mouthpiece seal structure of claim 1, wherein an inner ring front half mounting edge is provided on the inner ring front half (8) of the guide vane, and the inner ring front half mounting edge is connected to the inner ring front half mounting plate by a pin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211706483.8A CN115680789A (en) | 2022-12-29 | 2022-12-29 | Guide vane lower edge plate mouth-biting sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211706483.8A CN115680789A (en) | 2022-12-29 | 2022-12-29 | Guide vane lower edge plate mouth-biting sealing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115680789A true CN115680789A (en) | 2023-02-03 |
Family
ID=85056703
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211706483.8A Pending CN115680789A (en) | 2022-12-29 | 2022-12-29 | Guide vane lower edge plate mouth-biting sealing structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115680789A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140193243A1 (en) * | 2013-01-10 | 2014-07-10 | General Electric Company | Seal assembly for turbine system |
| CN205422834U (en) * | 2016-03-02 | 2016-08-03 | 哈尔滨工程大学 | Turbine that includes multiple rim seal structure of self -adaptation fumarole |
| CN109630210A (en) * | 2018-12-17 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of bite seal structure and the aero-engine with it |
| CN110905606A (en) * | 2019-12-05 | 2020-03-24 | 中国航发四川燃气涡轮研究院 | Turbine disc cavity sealing structure with bypass air entraining function |
| CN111255522A (en) * | 2020-01-19 | 2020-06-09 | 中国科学院工程热物理研究所 | Balance disc structure for adjusting axial force of high-pressure rotor system of engine |
| CN111441828A (en) * | 2020-03-12 | 2020-07-24 | 中国科学院工程热物理研究所 | Engine turbine disc cavity structure with prewhirl nozzle and flow guide disc |
| CN114876585A (en) * | 2022-06-08 | 2022-08-09 | 中国航发沈阳发动机研究所 | High-pressure turbine guide vane |
| CN114961869A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Rim sealing system and aeroengine |
-
2022
- 2022-12-29 CN CN202211706483.8A patent/CN115680789A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140193243A1 (en) * | 2013-01-10 | 2014-07-10 | General Electric Company | Seal assembly for turbine system |
| CN205422834U (en) * | 2016-03-02 | 2016-08-03 | 哈尔滨工程大学 | Turbine that includes multiple rim seal structure of self -adaptation fumarole |
| CN109630210A (en) * | 2018-12-17 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of bite seal structure and the aero-engine with it |
| CN110905606A (en) * | 2019-12-05 | 2020-03-24 | 中国航发四川燃气涡轮研究院 | Turbine disc cavity sealing structure with bypass air entraining function |
| CN111255522A (en) * | 2020-01-19 | 2020-06-09 | 中国科学院工程热物理研究所 | Balance disc structure for adjusting axial force of high-pressure rotor system of engine |
| CN111441828A (en) * | 2020-03-12 | 2020-07-24 | 中国科学院工程热物理研究所 | Engine turbine disc cavity structure with prewhirl nozzle and flow guide disc |
| CN114961869A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Rim sealing system and aeroengine |
| CN114876585A (en) * | 2022-06-08 | 2022-08-09 | 中国航发沈阳发动机研究所 | High-pressure turbine guide vane |
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Application publication date: 20230203 |
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| RJ01 | Rejection of invention patent application after publication |