CN113339078A - Flow deflector and processing method thereof - Google Patents
Flow deflector and processing method thereof Download PDFInfo
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- CN113339078A CN113339078A CN202110585812.7A CN202110585812A CN113339078A CN 113339078 A CN113339078 A CN 113339078A CN 202110585812 A CN202110585812 A CN 202110585812A CN 113339078 A CN113339078 A CN 113339078A
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- turbine blade
- air
- flow
- wall surface
- guide
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Classifications
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a flow deflector and a processing method thereof, wherein the flow deflector is provided with an air inlet cavity for cooling airflow to enter and an air guide hole for discharging the cooling airflow from the air inlet cavity, an annular airflow flow path is formed between the outer wall surface of the flow deflector and the inner wall surface of a turbine blade, and the cooling airflow in the air inlet cavity is discharged from the air guide hole and then flows to an exhaust hole of the turbine blade through the annular airflow flow path to be discharged, so that the cooling airflow flows in the annular airflow flow path and simultaneously uniformly cools the turbine blade. According to the guide vane, the cooling airflow flows in the annular airflow flow path, so that the cooling airflow is laid on the whole inner wall surface of the turbine blade, and is uniformly cooled and then discharged from the exhaust holes of the turbine blade, the effect of the cooling airflow on the turbine blade is improved, burning cracks caused by high-temperature burning during the operation of the turbine blade are effectively avoided, and the effective utilization rate of the cooling airflow is improved.
Description
Technical Field
The invention relates to the technical field of turbine blade cooling, in particular to a flow deflector and a machining method thereof.
Background
The turbine blade of the aircraft engine is positioned in an airflow channel with high temperature and high speed, the use environment of the blade is severe, and the turbine blade is easy to crack or break due to high-temperature ablation, so that the normal use of the engine is influenced. For this reason, the turbine blade is designed to be reliably used by introducing high-pressure cooling air from the front of the engine to cool the inner cavity of the turbine blade. However, the cooling air is merely introduced into the cavity of the turbine blade, but it is impossible to uniformly cool each portion of the turbine blade, and a part of the cooling air is discharged from the exhaust holes of the cavity of the turbine blade without sufficiently absorbing the heat of the turbine blade after entering the cavity of the turbine blade, so that the cooling effect is poor, and the turbine blade is still easily damaged at a high temperature.
Disclosure of Invention
The invention provides a flow deflector and a processing method thereof, and aims to solve the technical problems that the cooling effect of the existing turbine blade is poor, the cooling gas in the inner cavity of the turbine blade is not uniformly distributed, and part of the cooling gas does not fully cool the turbine blade.
According to one aspect of the invention, a flow deflector is provided for being inserted into an inner cavity of a turbine blade to guide and convey a cooling airflow into the inner cavity of the turbine blade, the flow deflector is provided with an air inlet cavity for the cooling airflow to enter and a bleed air hole for discharging the cooling airflow from the air inlet cavity, an annular airflow path is formed between an outer wall surface of the flow deflector and an inner wall surface of the turbine blade, and the cooling airflow in the air inlet cavity is discharged from the bleed air hole and then flows to an exhaust hole of the turbine blade through the annular airflow path, so that the cooling airflow uniformly cools the turbine blade while flowing through the annular airflow path.
Furthermore, the air guide holes on the guide vanes are close to the air inlet ends of the high-temperature air flows of the turbine blades, and the exhaust holes on the turbine blades are located at the air outlet ends of the high-temperature air flows of the turbine blades.
Furthermore, the flow deflector comprises a flow guide basin surface corresponding to the blade basin surface of the turbine blade, a flow guide back surface corresponding to the blade back surface of the turbine blade and a connection transition surface which is used for connecting the flow guide basin surface with the flow guide back surface and is opposite to the air inlet end of the turbine blade, and the air guide hole is formed in the connection transition surface.
Further, a plurality of the air guide holes are arranged along the depth direction of the annular airflow flow path.
Further, the air guide hole is a rectangular slot hole.
Furthermore, the outer wall surface of the guide vane, the inner wall surface of the turbine blade and the outer wall surface of the turbine blade have the same contour shape, and the size of the outer wall surface of the guide vane is smaller than that of the inner wall surface of the turbine blade, so that the annular airflow channel formed between the outer wall surface of the guide vane and the inner wall surface of the turbine blade has the same contour shape as that of the turbine blade.
Furthermore, the outer wall surface of the guide vane is provided with a bulge which is used for abutting against the inner wall surface of the turbine blade.
Further, the plurality of protrusions are arranged along the extending direction of the annular airflow flow path, and the plurality of protrusions are arranged along the depth direction of the annular airflow flow path.
Furthermore, the guide vane is provided with a mounting edge for supporting and fixing the opening of the inner cavity of the turbine blade.
According to another aspect of the present invention, there is provided a method for processing a guide vane, including the steps of: arranging an air guide hole at the design position of the metal sheet; processing the metal sheet into the shape of the unfolded flow deflector in a metal plate forming mode; the metal sheet is folded in half, and the bottom and the side of the metal sheet are welded and connected, so that the guide vane with the air inlet cavity is formed, and the opening of the air inlet cavity is located at the top of the guide vane.
The invention has the following beneficial effects:
the guide vane of the invention is inserted in the inner cavity of the turbine blade, so that an annular airflow flow path is formed between the outer wall surface of the guide vane and the inner wall surface of the turbine blade, and an air inlet cavity for cooling airflow to enter and an air guide hole for cooling airflow to be discharged from the air inlet cavity to the annular airflow flow path are arranged in the guide vane, therefore, the cooling airflow firstly enters the air inlet cavity of the guide vane and then enters the annular airflow flow path from the air guide hole, the cooling airflow flows in the annular airflow flow path, so that the cooling airflow is paved on the whole inner wall surface of the turbine blade, so that the cooling air flow uniformly cools the whole inner wall surface of the turbine blade and then is discharged from the exhaust hole of the turbine blade, thereby improving the effect of cooling the turbine blade by the cooling air flow, effectively avoiding the burning crack generated by high-temperature burning when the turbine blade works, and simultaneously improving the effective utilization rate of the cooling air flow.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a view illustrating a state of use of a guide vane according to a preferred embodiment of the present invention;
fig. 2 is a schematic structural view of a guide vane of a preferred embodiment of the present invention;
FIG. 3 is a schematic structural view of an air bleed hole according to a preferred embodiment of the present invention;
fig. 4 is an assembly angle view of a guide vane according to a preferred embodiment of the present invention;
FIG. 5 is a schematic view of the structure of the projection of the preferred embodiment of the present invention;
fig. 6 is a schematic view of the structure of the projection of the preferred embodiment of the present invention.
Illustration of the drawings:
1. a flow deflector; 2. an air inlet cavity; 3. an air vent; 4. a flow guide basin surface; 5. a flow guide back surface; 6. a protrusion; 7. installing edges; 8. a turbine blade; 9. and (4) exhausting holes.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
Fig. 1 is a view illustrating a state of use of a guide vane according to a preferred embodiment of the present invention; fig. 2 is a schematic structural view of a guide vane of a preferred embodiment of the present invention; FIG. 3 is a schematic structural view of an air bleed hole according to a preferred embodiment of the present invention; fig. 4 is an assembly angle view of a guide vane according to a preferred embodiment of the present invention; FIG. 5 is a schematic view of the structure of the projection of the preferred embodiment of the present invention; fig. 6 is a schematic view of the structure of the projection of the preferred embodiment of the present invention.
As shown in fig. 1, the baffle 1 of the present embodiment is configured to be inserted into an inner cavity of a turbine blade 8 to guide and convey a cooling airflow into the inner cavity of the turbine blade 8, the baffle is provided with an air inlet cavity 2 for the cooling airflow to enter and a bleed air hole 3 for the cooling airflow to be discharged from the air inlet cavity 2, an annular airflow path is formed between an outer wall surface of the baffle 1 and an inner wall surface of the turbine blade 8, and the cooling airflow in the air inlet cavity 2 is discharged from the bleed air hole 3 and then flows through the annular airflow path to an exhaust hole 9 of the turbine blade 8 to be discharged, so that the cooling airflow uniformly cools the turbine blade 8 while flowing through the annular airflow path. The guide vane 1 of the invention is inserted into the inner cavity of the turbine blade 8, so that an annular airflow flow path is formed between the outer wall surface of the guide vane 1 and the inner wall surface of the turbine blade 8, the air inlet cavity 2 for cooling airflow to enter and the air bleed holes 3 for cooling airflow to be discharged from the air inlet cavity 2 to the annular airflow flow path are arranged in the guide vane 1, so that the cooling airflow firstly enters the air inlet cavity 2 of the guide vane 1 and then enters the annular airflow flow path from the air bleed holes 3, the cooling airflow flows in the annular airflow flow path, the cooling airflow is paved on the whole inner wall surface of the turbine blade 8, and then the cooling airflow is uniformly cooled on the whole inner wall surface of the turbine blade 8 and then discharged from the exhaust holes 9 of the turbine blade 8, thereby improving the effect of the cooling airflow on cooling the turbine blade 8, and effectively avoiding the generation of cracks caused by high temperature when the turbine blade 8 works, and simultaneously, the effective utilization rate of the cooling air flow is improved.
As shown in fig. 1, 2 and 3, the air introducing holes 3 on the guide vane 1 are close to the inlet end of the high-temperature air flow of the turbine blade 8, and the air discharging holes 9 on the turbine blade 8 are located at the outlet end of the high-temperature air flow of the turbine blade 8. Because the temperature of the air inlet end of the high-temperature airflow of the turbine blade 8 is higher than that of the air outlet end, the air introducing holes 3 of the guide vane 1 are close to the air inlet end of the high-temperature airflow of the turbine blade 8, and the air exhaust holes 9 on the turbine blade 8 are located at the air outlet end of the high-temperature airflow of the turbine blade 8, so that the flowing direction of the cooling airflow in the annular airflow flow path is the same as that of the high-temperature airflow outside the turbine blade 8, the newly-entered cooling airflow firstly cools the air inlet end with the highest temperature on the vortex blade, then flows to the air outlet end of the turbine blade 8 to be exhausted, and simultaneously cools the inner wall surface of the turbine blade 8.
As shown in fig. 1, 2 and 3, the guide vane 1 includes a guide basin surface 4 corresponding to a blade basin surface of the turbine blade 8, a guide back surface 5 corresponding to a blade back surface of the turbine blade 8, and a connection transition surface connecting the guide basin surface 4 and the guide back surface 5 and facing the air inlet end of the turbine blade 8, and the air inlet hole 3 is opened on the connection transition surface. The connecting transition surface faces the turbine blade 8 at a position between the blade bowl surface and the blade back surface, i.e., the inlet end of the high-temperature air flow on the turbine blade 8. After the cooling airflow in the air intake cavity 2 enters the annular airflow flow path from the bleed air holes 3, a part of the cooling airflow flows along the blade bowl surface of the turbine blade 8 to the exhaust holes 9 on the exhaust end of the turbine blade 8 to be exhausted, so that the blade bowl surface of the turbine blade 8 is cooled, and a part of the cooling airflow flows along the blade back surface of the turbine blade 8 to the exhaust holes 9 on the exhaust end of the turbine blade 8 to be exhausted, so that the blade back surface of the turbine blade 8 is cooled.
As shown in fig. 2 and 3, the plurality of air holes 3 are arranged in the depth direction of the annular air flow path. The air vent 3 is a rectangular slot. In the present embodiment, three air holes 3 are arranged on the connection transition surface in the depth direction of the annular air flow path. The length dimension of the air guiding hole 3 is 7.5 mm. The width dimension of the air guiding hole 3 is 0.8 mm. The arrangement pitch between the air holes 3 is 10 mm.
Optionally, the connection transition surface is provided with a plurality of left air guiding holes 3, right air guiding holes 3 and middle air guiding holes 3 arranged along the depth direction of the annular airflow flow path. The middle air guiding hole 3 is opposite to the air inlet end of the turbine blade 8. The cooling air flow sprayed out from the left air guide hole 3 flows between the blade basin surface of the turbine blade 8 and the flow guide basin surface 4 of the flow guide sheet 1. The cooling air flow ejected from the right air guide hole 3 flows between the blade back surface of the turbine blade 8 and the guide back surface 5 of the guide vane 1. The cooling air flow sprayed out from the middle air guide hole 3 firstly flows to the air inlet end of the turbine blade 8, then flows into the annular air flow path from two sides, and finally is discharged from the air discharge hole 9 at the air outlet end of the turbine blade 8.
As shown in fig. 1, 2, and 4, the outer wall surface of the vane 1, the inner wall surface of the turbine blade 8, and the outer wall surface of the turbine blade 8 have the same contour shape, and the outer wall surface of the vane 1 has a size smaller than the inner wall surface of the turbine blade 8, so that the annular airflow passage formed between the outer wall surface of the vane 1 and the inner wall surface of the turbine blade 8 has the same contour shape as the turbine blade 8. In the present embodiment, the angle between the basic profile X-axis of the turbine blade 8 (i.e., perpendicular to the central axis of the turbine blade 8) and the rotational axis of the engine is 37 degrees. The angle between the X-axis of the guide vane 1 (i.e. perpendicular to the centre axis of the guide vane 1) and the axis of rotation of the engine is also 37 degrees.
As shown in fig. 2, 5, and 6, the outer wall surface of the guide vane 1 is provided with a projection 6 for abutting against the inner wall surface of the turbine blade 8. The plurality of projections 6 are arranged along the extending direction of the annular airflow path, and the plurality of projections 6 are arranged along the depth direction of the annular airflow path. The cooling air flows along the extension direction of the annular air flow path to the exhaust holes 9 for exhaust. The bulge 6 on the outer wall surface of the guide vane 1 is attached to the inner wall surface of the turbine blade 8, so that the guide vane 1 is stably installed, and the width of an annular airflow flow path between the guide vane 1 and the turbine blade 8 is ensured to be unchanged. In this embodiment, the protrusion 6 protrudes 0.5mm from the outer wall surface of the guide vane 1, and the width of the annular airflow path is 0.5 mm. Optionally, the protrusion 6 is circular with a radius of 4 mm. Optionally, the protrusions 6 are elongated. In this embodiment, the bottom of the baffle 1 is provided with two elongated protrusions 6. The upper part of the guide vane 1 is provided with 12 circular bulges 6.
As shown in fig. 1 and 5, the guide vane 1 is provided with a mounting edge 7 for supporting and fixing to an opening of an inner cavity of a turbine blade 8. The opening of the air inlet cavity 2 of the guide vane 1 is flanged outwards to form a mounting edge 7. The opening of the inner cavity of the turbine blade 8 is supported and fixed through the mounting edge 7, so that the guide vane 1 is stably mounted. Optionally, a mounting groove matched with the mounting edge 7 is arranged around the opening of the inner cavity of the turbine blade 8.
The method for processing the guide vane 1 of this embodiment is used for processing the guide vane 1, and includes the following steps: arranging an air vent 3 at the design position of the metal sheet; processing the metal sheet into the shape of the unfolded flow deflector 1 by adopting a metal plate forming mode; the metal sheet is folded in half, the bottom of the metal sheet is welded to the side of the metal sheet, and the side of the metal sheet is welded to the side of the metal sheet, so that the flow deflector 1 with the air inlet cavity 2 is formed, and the opening of the air inlet cavity 2 is located at the top of the flow deflector 1.
In this embodiment, the guide vane is made of a stainless steel sheet. The thickness of the stainless steel sheet was 0.3 mm. Firstly, determining the size of the flow deflector 1 after the flow deflector 1 is unfolded according to the design size of the flow deflector 1; then cutting the stainless steel sheet into a set size; a plurality of air holes 3 are formed in the positions, to be folded, of the stainless steel sheets; the two sides of the folded part of the stainless steel sheet are respectively processed into a flow guide basin surface 4 matched with a blade basin surface of the turbine blade 8 and a flow guide back surface 5 matched with a blade back surface of the turbine blade 8 in a sheet metal forming mode, and a plurality of bulges 6 are formed; then the stainless steel sheet is folded in half along the folding position to form the front edge of the guide vane 1, which is opposite to the air inlet end of the turbine blade 8, the bottom of the stainless steel sheet is welded in a side-to-side mode, and the side of the stainless steel sheet is welded in a side-to-side mode, so that the guide vane 1 with the air inlet cavity 2 is formed, and the opening of the air inlet cavity 2 is located at the top of the guide vane 1. The width of the weld seam formed by welding was 2.5 mm. In this embodiment, after the stainless steel sheet is folded in half, the bottom edge and the side edge of the flow guide basin surface 4 are attached to the inner side surface of the flow guide back surface 5, and then the bottom edge and the side edge of the flow guide basin surface 4 are welded and fixed to the inner side surface of the flow guide back surface 5.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A guide vane for insertion into the interior of a turbine blade (8) for guiding a cooling air flow for delivery to the interior of the turbine blade (8),
the flow deflector is provided with an air inlet cavity (2) for cooling air flow to enter and an air guide hole (3) for discharging the cooling air flow from the air inlet cavity (2), an annular air flow path is formed between the outer wall surface of the flow deflector (1) and the inner wall surface of the turbine blade (8),
the cooling airflow in the air inlet cavity (2) is discharged from the air guide holes (3) and then flows to the exhaust holes (9) of the turbine blades (8) through the annular airflow flow path to be discharged, so that the turbine blades (8) are uniformly cooled while the cooling airflow flows in the annular airflow flow path.
2. Flow deflector according to claim 1,
the air guide holes (3) on the guide vanes (1) are close to the air inlet ends of the high-temperature air flows of the turbine blades (8), and the exhaust holes (9) on the turbine blades (8) are located at the air outlet ends of the high-temperature air flows of the turbine blades (8).
3. Flow deflector according to claim 2,
the flow deflector (1) comprises a flow guide basin surface (4) corresponding to a leaf basin surface of the turbine blade (8), a flow guide back surface (5) corresponding to a leaf back surface of the turbine blade (8) and a connection transition surface which is used for connecting the flow guide basin surface (4) with the flow guide back surface (5) and is just opposite to an air inlet end of the turbine blade (8), and the air guide hole (3) is arranged on the connection transition surface.
4. Flow deflector according to claim 1,
the plurality of air guide holes (3) are arranged along the depth direction of the annular airflow flow path.
5. Flow deflector according to claim 1,
the air guide hole (3) is a rectangular long and narrow hole.
6. Flow deflector according to claim 1,
the outline shapes of the outer wall surface of the guide vane (1), the inner wall surface of the turbine blade (8) and the outer wall surface of the turbine blade (8) are the same, and the size of the outer wall surface of the guide vane (1) is smaller than that of the inner wall surface of the turbine blade (8), so that the annular airflow flow path formed between the outer wall surface of the guide vane (1) and the inner wall surface of the turbine blade (8) is the same as the outline shape of the turbine blade (8).
7. Flow deflector according to claim 1,
the outer wall surface of the guide vane (1) is provided with a bulge (6) which is used for abutting against the inner wall surface of the turbine blade (8).
8. Flow deflector according to claim 7,
the plurality of protrusions (6) are arranged along the extending direction of the annular airflow flow path, and the plurality of protrusions (6) are arranged along the depth direction of the annular airflow flow path.
9. Flow deflector according to claim 1,
the guide vane (1) is provided with a mounting edge (7) which is used for supporting and fixing the opening of the inner cavity of the turbine blade (8).
10. A method for manufacturing a guide vane for a flow guide vane (1) according to any one of claims 1 to 9, comprising the steps of:
arranging an air guide hole (3) at the design position of the metal sheet;
processing the metal sheet into the shape of the unfolded flow deflector (1) by adopting a metal plate forming mode;
the method comprises the following steps of folding a metal sheet in half, and welding and connecting the bottom and the side of the metal sheet, so that a flow deflector (1) with an air inlet cavity (2) is formed, and the opening of the air inlet cavity (2) is located at the top of the flow deflector (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110585812.7A CN113339078B (en) | 2021-05-27 | 2021-05-27 | Flow deflector and processing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110585812.7A CN113339078B (en) | 2021-05-27 | 2021-05-27 | Flow deflector and processing method thereof |
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| Publication Number | Publication Date |
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| CN113339078A true CN113339078A (en) | 2021-09-03 |
| CN113339078B CN113339078B (en) | 2022-12-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110585812.7A Active CN113339078B (en) | 2021-05-27 | 2021-05-27 | Flow deflector and processing method thereof |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030143064A1 (en) * | 2001-12-05 | 2003-07-31 | Snecma Moteurs | Nozzle-vane band for a gas turbine engine |
| EP1635040A1 (en) * | 2004-09-08 | 2006-03-15 | BorgWarner Inc. | Method of assembling a variable inlet guide vane assembly and jig therefor |
| CN102943711A (en) * | 2012-11-12 | 2013-02-27 | 湖南航翔燃气轮机有限公司 | Device for cooling guiding device group of turbine |
| CN107013249A (en) * | 2015-10-20 | 2017-08-04 | 通用电气公司 | Wheel space purging stream mixing chamber |
| CN112814948A (en) * | 2020-12-31 | 2021-05-18 | 西安汇腾航空科技有限公司 | Aeroengine flow deflector and manufacturing method thereof |
-
2021
- 2021-05-27 CN CN202110585812.7A patent/CN113339078B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030143064A1 (en) * | 2001-12-05 | 2003-07-31 | Snecma Moteurs | Nozzle-vane band for a gas turbine engine |
| EP1635040A1 (en) * | 2004-09-08 | 2006-03-15 | BorgWarner Inc. | Method of assembling a variable inlet guide vane assembly and jig therefor |
| CN102943711A (en) * | 2012-11-12 | 2013-02-27 | 湖南航翔燃气轮机有限公司 | Device for cooling guiding device group of turbine |
| CN107013249A (en) * | 2015-10-20 | 2017-08-04 | 通用电气公司 | Wheel space purging stream mixing chamber |
| CN112814948A (en) * | 2020-12-31 | 2021-05-18 | 西安汇腾航空科技有限公司 | Aeroengine flow deflector and manufacturing method thereof |
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| CN113339078B (en) | 2022-12-16 |
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