CN112483191B - Turbine blade suitable for gas turbine possesses heat convection function - Google Patents
Turbine blade suitable for gas turbine possesses heat convection function Download PDFInfo
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- CN112483191B CN112483191B CN202011370851.7A CN202011370851A CN112483191B CN 112483191 B CN112483191 B CN 112483191B CN 202011370851 A CN202011370851 A CN 202011370851A CN 112483191 B CN112483191 B CN 112483191B
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- heat exchange
- turbine blade
- circular
- convection
- exchange chamber
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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
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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
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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
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a turbine blade with a convection heat exchange function and suitable for a gas turbine, relates to the technical field of turbine blades, and solves the problems that heat in the turbine blade cannot be efficiently exchanged and output due to poor heat exchange effect of the conventional turbine blade, and the turbine blade is damaged due to high heat load in long-time application. The utility model provides a turbine blade suitable for gas turbine possesses convection heat transfer function, includes turbine blade, a convection heat transfer cavity has been seted up to the inside blade body middle part of turbine blade. The air flow in the convection heat exchange cavity is input by continuous air flow at the circular air flow channel A and the circular air flow channel B, and the air flow in the convection heat exchange cavity is flushed to open the cutting opening of the circular rubber sheet in the circular heat dissipation channel, so that the air flow in the convection heat exchange cavity is discharged out of the convection heat exchange cavity from the cutting opening of the circular rubber sheet, and the heat exchange output of the heat in the turbine blade is realized.
Description
Technical Field
The invention belongs to the technical field of turbine blades, and particularly relates to a turbine blade with a convection heat exchange function, which is suitable for a gas turbine.
Background
Turbine blades are important components of the turbine section of a gas turbine engine. The blades rotating at high speed are responsible for drawing high-temperature and high-pressure air flow into the combustor to maintain the operation of the engine. In order to ensure stable and long-term operation in extreme environments of high temperature and high pressure, turbine blades are often forged from high temperature alloys and are cooled in different ways, such as internal air flow cooling, boundary layer cooling, or thermal barrier coatings protecting the blades, to ensure operational reliability.
For example, application No.: 201310452739.1 the invention discloses a turbine blade and a turbine and an engine with the same, the leading edge of the turbine blade is provided with a first cavity, the leading edge of the turbine blade is provided with a first air inlet communicated with the first cavity, and the suction surface and the pressure surface of the front edge of the turbine blade are respectively provided with at least one air film hole which is communicated with the first cavity, a second cavity is formed in the middle of the turbine blade, at least two clapboards are arranged in the second cavity to limit an S-shaped channel, a second air inlet communicated with the S-shaped channel is formed in the middle of the turbine blade, and the second air inlet is adjacent to the leading edge of the turbine blade, and a plurality of exhaust holes communicated with the S-shaped channel are formed on the pressure surface at the trailing edge of the turbine blade and extend towards the direction of the trailing edge. The turbine blade is simple to machine and high in cooling efficiency.
Based on the search of the above patents and the discovery of the combination of the devices in the prior art, with the rapid development of the aircraft engine technology, no matter the pressure ratio of the compressor of the aircraft engine and the temperature of the front inlet of the turbine are both greatly increased, the thermal load on the turbine blade is sharply increased, and the turbine blade is subjected to very serious thermal stress, but the heat exchange effect of the existing turbine blade is not good, so that the heat inside the turbine blade cannot be efficiently exchanged and output, and the turbine blade is damaged due to high thermal load in long-time application.
Disclosure of Invention
In order to solve the technical problems, the invention provides a turbine blade with a convective heat exchange function, which is suitable for a gas turbine, so as to solve the problems that the heat in the turbine blade cannot be efficiently output in a heat exchange manner due to poor heat exchange effect of the conventional turbine blade, and the turbine blade is damaged due to high heat load in long-time application.
The invention relates to a purpose and an effect of a turbine blade with a convection heat exchange function, which are suitable for a gas turbine, and the purpose and the effect are achieved by the following specific technical means:
a turbine blade with a convection heat exchange function suitable for a gas turbine comprises a turbine blade, wherein a convection heat exchange chamber is formed in the middle of the blade body in the turbine blade; the convection heat exchange cavity comprises a circular heat dissipation channel, stop blocks, circular rubber sheets and a fracture, the outer end face of the turbine blade is provided with a circular heat dissipation channel communicated with the convection heat exchange cavity relative to the part of the convection heat exchange cavity, the inner circumference of the circular heat dissipation channel is provided with four stop blocks in an annular array shape, the inner circumference of the circular heat dissipation channel is hermetically bonded with one circular rubber sheet with the same diameter as the circular rubber sheet, and the bottom end face of the circular rubber sheet is contacted with the four stop blocks; the tail end part of the blade body in the turbine blade is provided with a second heat exchange chamber, and the head end part of the blade body in the turbine blade is provided with a first heat exchange chamber.
Furthermore, the first heat exchange chamber comprises a first airflow communication channel and a bearing A, the first heat exchange chamber is communicated with the head end part of the blade body on the inner peripheral surface of the turbine blade through the first airflow communication channel, a group of bearings A is embedded in the top surface and the bottom surface of the inner end of the first heat exchange chamber, and the two groups of bearings A are located on the same axis.
Furthermore, the first heat exchange chamber comprises a rotating shaft A and straight plate blades A, the rotating shaft A is jointly installed between the two groups of bearings A, the periphery of the rotating shaft A is in an annular array shape, and the four straight plate blades A are arranged, and are not in contact with the inner end face of the first heat exchange chamber.
Furthermore, the second heat exchange chamber comprises a second air flow communication channel and a bearing B, the second heat exchange chamber is communicated with the head end part of the blade body on the inner peripheral surface of the turbine blade through the second air flow communication channel, a group of bearings B is embedded in the top surface and the bottom surface of the inner end of the second heat exchange chamber, and the two groups of bearings B are located on the same axis.
Furthermore, the second heat exchange chamber comprises a rotating shaft B and straight plate blades B, the rotating shaft B is jointly installed between the two groups of bearings B, the outer periphery of the rotating shaft B is in an annular array shape, and the four straight plate blades B are arranged, and are not in contact with the inner end face of the second heat exchange chamber.
Further, the convection heat exchange cavity comprises a cylindrical protrusion A, a circular airflow channel A, a cylindrical protrusion B and a circular airflow channel B, the end face in the convection heat exchange cavity is provided with the cylindrical protrusion A relative to the first heat exchange cavity, the axis position of the cylindrical protrusion A is provided with the circular airflow channel A communicated with the first heat exchange cavity and the convection heat exchange cavity, the end face in the convection heat exchange cavity is provided with the cylindrical protrusion B relative to the second heat exchange cavity, and the axis position of the cylindrical protrusion B is provided with the circular airflow channel B communicated with the second heat exchange cavity and the convection heat exchange cavity.
Furthermore, the cylindrical protrusion A and the cylindrical protrusion B are in the same axis state, and the distance between the cylindrical protrusion A and the cylindrical protrusion B is ten centimeters.
Further, the convection heat transfer cavity is including cutting the mouth, and a cutting off mouth has been seted up at circular rubber thin slice axle center position, and the cutting off mouth is the cruciform structure, is in sealed closed state under the cutting off mouth ordinary state, and the cutting off position that is the cutting off mouth of cruciform structure is the interval form with four dogs and distributes.
Compared with the prior art, the invention has the following beneficial effects:
when the turbine blade is applied, airflow respectively enters from the opening ends of the first airflow communication channel and the second airflow communication channel at the head end parts of the blade bodies on the inner circumferential surfaces of the turbine blades, the airflow entering from the opening ends of the first airflow communication channels is input into the first heat exchange cavity, and the entering airflow blows the straight plate blades A to rotate along the bearing A through the rotating shaft A, so that the airflow in the first heat exchange cavity is stirred, and the efficient airflow heat exchange in the first heat exchange cavity is realized; and the air flow entering from the open end part of the second air flow communication channel is input into the second heat exchange cavity, and the entering air flow blows the straight plate blade B to rotate along the bearing B through the rotating shaft B, so that the air flow in the second heat exchange cavity is stirred, and the high-efficiency air flow heat exchange in the second heat exchange cavity is realized.
The heat-exchanged air flow in the first heat exchange cavity is input into the convection heat exchange cavity through the circular air flow channel A, and the heat-exchanged air flow in the second heat exchange cavity is input into the convection heat exchange cavity through the circular air flow channel B; according to the invention, the distance between the cylindrical protrusion A and the cylindrical protrusion B is ten centimeters, so that the air flow input into the convection heat exchange cavity from the circular air flow channel A and the air flow input into the convection heat exchange cavity from the circular air flow channel B are opposite to each other, and convection is realized, so that the air flow in the convection heat exchange cavity is stirred more efficiently, and efficient air flow heat exchange in the convection heat exchange cavity is realized; the air flow in the convection heat exchange cavity is input by continuous air flow at the circular air flow channel A and the circular air flow channel B, and the air flow in the convection heat exchange cavity is flushed to open the cutting opening of the circular rubber sheet in the circular heat dissipation channel, so that the air flow in the convection heat exchange cavity is discharged out of the convection heat exchange cavity from the cutting opening of the circular rubber sheet, and the heat exchange output of the heat in the turbine blade is realized.
Drawings
FIG. 1 is a cross-sectional structural schematic view of a turbine blade of the present invention.
FIG. 2 is a schematic structural view of the present invention in FIG. 1 with the rotation axis A, the circular rubber sheet and the rotation axis B removed.
Fig. 3 is a partial enlarged structure schematic diagram of a second heat exchange chamber part of the invention.
Fig. 4 is a partial enlarged structural schematic view of a first heat exchange chamber part of the invention.
Fig. 5 is a partially enlarged structural view of the convection heat exchange chamber of the present invention.
Fig. 6 is a partially enlarged structural view of the circular heat dissipation channel portion of the present invention.
Fig. 7 is a schematic view of the structure of the invention in the direction a in fig. 6.
In the drawings, the corresponding relationship between the component names and the reference numbers is as follows:
1. a turbine blade; 2. a first heat exchange chamber; 201. a first gas flow communication channel; 202. a bearing A; 203. a rotating shaft A; 204. a straight blade A; 3. a convective heat exchange chamber; 301. a cylindrical protrusion A; 302. a circular airflow channel A; 303. a cylindrical protrusion B; 304. a circular gas flow channel B; 305. a circular heat dissipation channel; 306. a stopper; 307. a circular rubber sheet; 308. cutting off the port; 4. a second heat exchange chamber; 401. a second gas flow communication channel; 402. a bearing B; 403. a rotating shaft B; 404. straight blade B.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "upper", "lower", "left", "right", "inner", "outer", "front", "rear", "head", "tail", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are only for convenience in describing and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the terms "connected" and "connected" are to be interpreted broadly, e.g., as being fixed or detachable or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example (b):
as shown in figures 1 to 7:
the invention provides a turbine blade with a convection heat exchange function, which is suitable for a gas turbine and comprises the following components: the middle part of the blade body inside the turbine blade 1 is provided with a convection heat exchange chamber 3; the convection heat exchange chamber 3 comprises a circular heat dissipation channel 305, a stop block 306, circular rubber sheets 307 and a cut-off port 308, the outer end surface of the turbine blade 1 is provided with a circular heat dissipation channel 305 communicated with the convection heat exchange chamber 3, the inner circumferential surface of the circular heat dissipation channel 305 is provided with four stop blocks 306 in an annular array shape, the inner circumferential surface of the circular heat dissipation channel 305 is hermetically bonded with one circular rubber sheet 307 with the same diameter as the circular heat dissipation channel, and the bottom end surface of the circular rubber sheet 307 is contacted with the four stop blocks 306; the tail end part of the blade body in the turbine blade 1 is provided with a second heat exchange chamber 4, and the head end part of the blade body in the turbine blade 1 is provided with a first heat exchange chamber 2.
The first heat exchange chamber 2 comprises a first airflow communication channel 201 and a bearing A202, the first heat exchange chamber 2 is communicated with the head end part of the blade body on the inner circumferential surface of the turbine blade 1 through the first airflow communication channel 201, a group of bearings A202 is embedded in the top surface and the bottom surface of the inner end of the first heat exchange chamber 2, and the two groups of bearings A202 are located on the same axis.
The first heat exchange chamber 2 comprises a rotating shaft A203 and straight plate blades A204, the rotating shaft A203 is installed between the two groups of bearings A202, the outer peripheral surface of the rotating shaft A203 is in an annular array shape, four straight plate blades A204 are arranged, and the four straight plate blades A204 are not in contact with the inner end surface of the first heat exchange chamber 2.
The second heat exchange chamber 4 comprises a second airflow communication channel 401 and a bearing B402, the second heat exchange chamber 4 is communicated with the head end part of the blade body on the inner circumferential surface of the turbine blade 1 through the second airflow communication channel 401, a group of bearings B402 is embedded in the top surface and the bottom surface of the inner end of the second heat exchange chamber 4, and the two groups of bearings B402 are located on the same axis.
The second heat exchange chamber 4 comprises a rotating shaft B403 and straight blades B404, the rotating shaft B403 is installed between the two groups of bearings B402, the four straight blades B404 are arranged on the outer periphery of the rotating shaft B403 in an annular array, and the four straight blades B404 are not in contact with the inner end face of the second heat exchange chamber 4.
The convection heat exchange cavity 3 comprises a cylindrical protrusion A301, a circular airflow channel A302, a cylindrical protrusion B303 and a circular airflow channel B304, the end surface in the convection heat exchange cavity 3 is provided with a cylindrical protrusion A301 relative to the position of the first heat exchange cavity 2, the axis position of the cylindrical protrusion A301 is provided with a circular airflow channel A302 communicated with the first heat exchange cavity 2 and the convection heat exchange cavity 3, the end surface in the convection heat exchange cavity 3 is provided with a cylindrical protrusion B303 relative to the position of the second heat exchange cavity 4, and the axis position of the cylindrical protrusion B303 is provided with a circular airflow channel B304 communicated with the second heat exchange cavity 4 and the convection heat exchange cavity 3.
The cylindrical bulge A301 and the cylindrical bulge B303 are in the same axis state, and the distance between the cylindrical bulge A301 and the cylindrical bulge B303 is ten centimeters.
The convection heat exchange chamber 3 comprises a cutting opening 308, the axis part of the circular rubber sheet 307 is provided with one cutting opening 308, the cutting opening 308 is in a cross structure, the cutting opening 308 is in a sealed closed state under a common state, and the cutting part of the cutting opening 308 in the cross structure and the four stoppers 306 are distributed at intervals.
When in use:
when the heat exchange device is used, airflow respectively enters from the opening ends of the first airflow communication channel 201 and the second airflow communication channel 401 at the head end of the blade body on the inner circumferential surface of the turbine blade 1, the airflow entering from the opening end of the first airflow communication channel 201 is input into the first heat exchange chamber 2, and the entering airflow blows the straight plate blade A204 to rotate along the bearing A202 through the rotating shaft A203, so that the airflow in the first heat exchange chamber 2 is stirred, and the efficient airflow heat exchange in the first heat exchange chamber 2 is realized; the air flow entering from the open end of the second air flow communication channel 401 is input into the second heat exchange chamber 4, and the entering air flow blows the straight plate blade B404 to rotate along the bearing B402 through the rotating shaft B403, so that the air flow in the second heat exchange chamber 4 is stirred, and the efficient air flow heat exchange in the second heat exchange chamber 4 is realized;
the heat-exchanged air flow in the first heat exchange chamber 2 is input into the convective heat exchange chamber 3 through the circular air flow channel a302, and the heat-exchanged air flow in the second heat exchange chamber 4 is input into the convective heat exchange chamber 3 through the circular air flow channel B304; because the distance between the cylindrical bulge A301 and the cylindrical bulge B303 is ten centimeters, the air flow input into the convection heat exchange chamber 3 from the circular air flow channel A302 and the air flow input into the convection heat exchange chamber 3 from the circular air flow channel B304 are opposite to each other, so that convection is realized, the air flow in the convection heat exchange chamber 3 is stirred more efficiently, and efficient air flow heat exchange in the convection heat exchange chamber 3 is realized;
and under the input of the continuous air flow at the circular air flow channel a302 and the circular air flow channel B304, the air flow inside the convective heat exchange chamber 3 will break the cut-off 308 of the circular rubber sheet 307 sealed in the circular heat dissipation channel 305, so that the air flow inside the convective heat exchange chamber 3 is discharged from the cut-off 308 of the circular rubber sheet 307 out of the convective heat exchange chamber 3, and the heat exchange output inside the turbine blade 1 is realized.
The embodiments of the present invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiment was chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.
Claims (4)
1. The utility model provides a turbine blade that is applicable to gas turbine possesses heat convection function which characterized in that: the turbine blade comprises a turbine blade (1), wherein a convection heat exchange chamber (3) is formed in the middle of a blade body in the turbine blade (1); the convection heat exchange cavity (3) comprises a circular heat dissipation channel (305), stop blocks (306), circular rubber sheets (307) and a cut-off (308), the outer end face of the turbine blade (1) is provided with a circular heat dissipation channel (305) communicated with the convection heat exchange cavity (3) relative to the part of the convection heat exchange cavity, the inner circumferential surface of the circular heat dissipation channel (305) is provided with four stop blocks (306) in an annular array shape, the inner circumferential surface of the circular heat dissipation channel (305) is hermetically bonded with one circular rubber sheet (307) with the same diameter as the circular heat dissipation channel, and the bottom end faces of the circular rubber sheets (307) are in contact with the four stop blocks (306); the tail end part of the blade body in the turbine blade (1) is provided with a second heat exchange chamber (4), and the head end part of the blade body in the turbine blade (1) is provided with a first heat exchange chamber (2);
the first heat exchange chamber (2) comprises a rotating shaft A (203) and straight plate blades A (204), one rotating shaft A (203) is installed between two groups of bearings A (202), the outer peripheral surface of the rotating shaft A (203) is in an annular array shape, four straight plate blades A (204) are arranged, and the four straight plate blades A (204) are not in contact with the inner end surface of the first heat exchange chamber (2);
the second heat exchange chamber (4) comprises a rotating shaft B (403) and straight-plate blades B (404), one rotating shaft B (403) is installed between two groups of bearings B (402), the outer peripheral surface of the rotating shaft B (403) is in an annular array shape, four straight-plate blades B (404) are arranged, and the four straight-plate blades B (404) are not in contact with the inner end surface of the second heat exchange chamber (4);
the convection heat exchange cavity (3) comprises a cylindrical protrusion A (301), a circular airflow channel A (302), a cylindrical protrusion B (303) and a circular airflow channel B (304), the inner end face of the convection heat exchange cavity (3) is provided with the cylindrical protrusion A (301) relative to the first heat exchange cavity (2), the axis of the cylindrical protrusion A (301) is provided with the circular airflow channel A (302) communicated with the first heat exchange cavity (2) and the convection heat exchange cavity (3), the inner end face of the convection heat exchange cavity (3) is provided with the cylindrical protrusion B (303) relative to the second heat exchange cavity (4), and the axis of the cylindrical protrusion B (303) is provided with the circular airflow channel B (304) communicated with the second heat exchange cavity (4) and the convection heat exchange cavity (3);
the cylindrical protrusion A (301) and the cylindrical protrusion B (303) are in the same axis state, and the distance between the cylindrical protrusion A (301) and the cylindrical protrusion B (303) is ten centimeters.
2. The turbine blade with a heat convection function for a gas turbine as set forth in claim 1, wherein: the first heat exchange chamber (2) comprises a first airflow communication channel (201) and a bearing A (202), the first heat exchange chamber (2) is communicated with the head end part of the blade body on the inner circumferential surface of the turbine blade (1) through the first airflow communication channel (201), a group of bearings A (202) are embedded in the top surface and the bottom surface of the inner end of the first heat exchange chamber (2), and the two groups of bearings A (202) are located on the same axis.
3. A turbine blade adapted for use in a gas turbine engine and having convective heat transfer capability in accordance with claim 1, wherein: the second heat exchange chamber (4) comprises a second airflow communication channel (401) and bearings B (402), the second heat exchange chamber (4) is communicated with the head end of the blade body on the inner circumferential surface of the turbine blade (1) through the second airflow communication channel (401), a group of bearings B (402) are embedded in the top surface and the bottom surface of the inner end of the second heat exchange chamber (4), and the two groups of bearings B (402) are located on the same axis.
4. The turbine blade with a heat convection function for a gas turbine as set forth in claim 1, wherein: the convection heat exchange cavity (3) comprises a cutting opening (308), the axis part of the circular rubber sheet (307) is provided with the cutting opening (308), the cutting opening (308) is of a cross structure, the cutting opening (308) is in a sealed closed state under a common state, and the cutting part of the cutting opening (308) of the cross structure and the four stop blocks (306) are distributed at intervals.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011370851.7A CN112483191B (en) | 2020-11-30 | 2020-11-30 | Turbine blade suitable for gas turbine possesses heat convection function |
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| CN202011370851.7A CN112483191B (en) | 2020-11-30 | 2020-11-30 | Turbine blade suitable for gas turbine possesses heat convection function |
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| CN112483191B true CN112483191B (en) | 2022-07-19 |
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| CN207526530U (en) * | 2017-05-19 | 2018-06-22 | 南京航空航天大学 | A kind of efficient cooling blade of gas-turbine unit |
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| NL73916C (en) * | 1949-07-06 | 1900-01-01 | ||
| US5667359A (en) * | 1988-08-24 | 1997-09-16 | United Technologies Corp. | Clearance control for the turbine of a gas turbine engine |
| FR2659689B1 (en) * | 1990-03-14 | 1992-06-05 | Snecma | INTERNAL COOLING CIRCUIT OF A TURBINE STEERING BLADE. |
| DE19738065A1 (en) * | 1997-09-01 | 1999-03-04 | Asea Brown Boveri | Turbine blade of a gas turbine |
| US6890154B2 (en) * | 2003-08-08 | 2005-05-10 | United Technologies Corporation | Microcircuit cooling for a turbine blade |
| WO2009016744A1 (en) * | 2007-07-31 | 2009-02-05 | Mitsubishi Heavy Industries, Ltd. | Wing for turbine |
| CN210502316U (en) * | 2019-07-17 | 2020-05-12 | 深圳市速易停车库运营管理有限公司 | Charging pile with heat dissipation grid based on new energy automobile |
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| CN207526530U (en) * | 2017-05-19 | 2018-06-22 | 南京航空航天大学 | A kind of efficient cooling blade of gas-turbine unit |
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