CN112648018A - High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade - Google Patents
High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade Download PDFInfo
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- CN112648018A CN112648018A CN202011386035.5A CN202011386035A CN112648018A CN 112648018 A CN112648018 A CN 112648018A CN 202011386035 A CN202011386035 A CN 202011386035A CN 112648018 A CN112648018 A CN 112648018A
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- blade
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- root
- engine
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- 238000001816 cooling Methods 0.000 title claims abstract description 32
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 11
- 239000000956 alloy Substances 0.000 title claims abstract description 11
- 229910000601 superalloy Inorganic materials 0.000 claims description 7
- 125000003003 spiro group Chemical group 0.000 claims description 5
- 238000007664 blowing Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000011148 porous material Substances 0.000 description 5
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004568 cement Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Images
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
-
- 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
- F01D5/186—Film cooling
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a high-temperature alloy blade for an engine, which can ensure the efficient cooling of the front edge of the blade, relates to the technical field of blade cooling, and aims to solve the problems that the existing blade cooling mode is mostly an active cooling mode, cold air is input by separating part of power of the engine, so that the load of the engine is increased, the service life of the engine is shortened, the air film cooling efficiency on the blade is greatly influenced by the blowing ratio and the Reynolds coefficient, and the contact time of the cold air and the tail end of the blade is short; the root of the blade main body is fixedly provided with a blade tenon root; the left side and the right side of the joint of the blade tenon root and the blade main body are respectively and fixedly provided with an arc-shaped skirt, and the blade main body is inserted between the skirts. According to the invention, the outer convex blade tail edge guide strips are uniformly and fixedly arranged at the tail end edge of the blade main body along the outer surface at intervals, so that the aim of rapid cooling is fulfilled.
Description
Technical Field
The invention relates to the technical field of blade cooling, in particular to a high-temperature alloy blade for an engine, which can ensure the efficient cooling of the front edge of the blade.
Background
The engine is a rotary power machine that converts the energy of steam into mechanical work, and is also called a steam turbine. The engine is mainly used as a prime mover for power generation, can directly drive various pumps, fans, compressors, ship propellers and the like, and can meet the heat supply requirements in production and life by utilizing the exhaust steam or intermediate extraction steam of the engine. The engine is mainly applied to the fields of electric power industry, ship industry, cement, chemical industry, petroleum, metallurgy, heavy machinery and the like.
A low-cost superalloy steam turbine blade in patent application CN201810585644.X relates to power generation equipment technical field, including blade root, blade profile and the blade shroud of fixed connection in proper order, the blade profile is variable cross section distortion structure, one side of blade profile is the air inlet edge, and the opposite side is the air outlet edge, the one end of blade shroud is provided with the draw-in groove, the width direction of the notch orientation blade shroud of draw-in groove, the other end of blade shroud be provided with draw-in groove assorted fixture block, two adjacent blade shrouds pass through draw-in groove and fixture block cooperation realization connection. The invention also discloses a preparation method of the low-cost high-temperature alloy turbine blade, which is higher in mechanical property than the existing turbine blade, more resistant to high temperature and greatly prolonged in service life.
The existing blade cooling mode is mostly an active cooling mode, and the input of cold air is carried out through a part of power of a separation engine, so that the load of the engine is increased, the service life is shortened, the influence of the blowing ratio on the air film cooling efficiency of the blade is large, the influence of the part of the Reynolds coefficient is also influenced, and the contact time of the cold air and the tail end of the blade is short.
In view of the above, the present invention provides a high temperature alloy blade for an engine, which can ensure efficient cooling of the front edge of the blade, by improving the conventional structure and defects, so as to achieve the purpose of higher practical value.
Disclosure of Invention
In order to solve the technical problems, the invention provides a high-temperature alloy blade for an engine, which can ensure the efficient cooling of the front edge of the blade, and aims to solve the problems that the existing blade cooling mode is mostly an active cooling mode, the load of the engine is increased, the service life of the engine is shortened by inputting cold air by separating part of power of the engine, the air film cooling efficiency on the blade is greatly influenced by the blowing ratio and the Reynolds coefficient, and the contact time of the cold air and the tail end of the blade is short.
The invention can ensure the purpose and the effect of the high-temperature alloy blade for the engine with the efficiently cooled blade front edge, and is achieved by the following specific technical means:
the high-temperature alloy blade for the engine, which can ensure the efficient cooling of the front edge of the blade, comprises a blade main body; the root of the blade main body is fixedly provided with a blade tenon root; the left side and the right side of the joint of the blade tenon root and the blade main body are respectively and fixedly provided with an arc-shaped skirt, and the blade main body is inserted between the skirts.
Further, the blade main body comprises a blade trailing edge guide strip and an air film hole, the outer convex blade trailing edge guide strip is uniformly and fixedly installed at the edge of the tail end of the blade main body along the outer surface at intervals, the air film hole with uniform intervals is vertically formed in the blade main body, and the root and the top of the blade main body are communicated through the air film hole.
Further, the skirt includes spoiler, intercommunicating pore, fixed ear seat and fixing bolt, there are four spoilers at even interval along curved surface fixed mounting on the cambered surface of skirt top, and set up the intercommunicating pore at even interval on the skirt between the spoiler, equal fixed mounting has fixed ear seat in both ends and middle part position department about the cambered surface of skirt bottom, and staggers mutually in proper order about three fixed ear seat, and equal spiro union has fixing bolt perpendicularly in the fixed ear seat.
Further, blade tenon root includes tenon and drainage plate, the lower extreme border department fixed mounting of blade tenon root has the tenon of T type form, and the left end position department of blade tenon root front end cambered surface wall and rear end cambered surface wall fixed mounting respectively has cambered surface form drainage plate, and the interior concave surface of drainage plate is right.
Furthermore, the skirt main body is of an inclined plane structure with a high left end and a low right end, and the skirt is of an arc surface structure with a forward concave surface.
Further, the mass flow ratio of the jet flow between the guide strips at the tail edge of the blade is 1.14-6.4, and the Reynolds coefficient of the jet flow is 8000-48000.
Further, the rotational twist angle of the blade body is sixty degrees.
Compared with the prior art, the invention has the following beneficial effects:
because the tail end border department of blade body has the blade trailing edge gib block of evagination along the even fixed mounting in surface interval, the even air film hole in interval has been seted up vertically in the blade body, its air film hole is linked together blade body root and top, after cold air got into from blade tenon root, cold air partly flows along the blade body, partly enters into the air film hole of blade body, spray through the air film that produces and cool off the blade leading edge with air film overflow effect, and the cold air through blade trailing edge gib block can cool off the blade back cheek district of blade body, so that reach quick refrigerated purpose.
Because four spoilers that the interval is even are installed along crooked fixed surface to the cambered surface in skirt top, and set up the intercommunicating pore that the interval is even on the skirt between the spoilers, both ends and the equal fixed mounting in middle part position department have fixed ear seat about the cambered surface of skirt bottom, and the three fixed ear seat is controlled and is staggered mutually in proper order, and equal perpendicular spiro union has fixing bolt in the fixed ear seat, and the blade main part is at rotatory in-process, can make the cold air of entering cut-off and can be to the edge guide to improve cooling efficiency.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
FIG. 1 is a schematic view of the right front upper side axial view of the assembled state of the present invention.
FIG. 2 is a schematic view of the assembled left-rear-upper axial view of the present invention.
FIG. 3 is a schematic view of the left rear lower axial view of the assembled state of the present invention.
Fig. 4 is a schematic front view of the present invention.
Fig. 5 is a partial sectional structural view of a-a in fig. 4 according to the present invention.
Fig. 6 is a right-view structural diagram of the present invention.
In the drawings, the corresponding relationship between the component names and the reference numbers is as follows:
1. a blade main body; 101. a blade trailing edge guide strip; 102. a gas film hole; 2. a skirt; 201. a spoiler; 202. a communicating hole; 203. fixing the ear seat; 204. fixing the bolt; 3. a blade dovetail root; 301. a tenon; 302. a drainage plate.
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 is to be noted that, unless otherwise explicitly specified or limited, 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 6:
the invention provides a high-temperature alloy blade for an engine, which can ensure the efficient cooling of the front edge of the blade, and comprises a blade main body 1; the root of the blade main body 1 is fixedly provided with a blade tenon root 3; the left side and the right side of the joint of the blade tenon root 3 and the blade main body 1 are respectively and fixedly provided with an arc-shaped skirt 2, and the blade main body 1 is inserted between the skirt 2; skirt 2 includes spoiler 201, the intercommunicating pore 202, fixed ear seat 203 and fixing bolt 204, there are four spoilers 201 of interval even along curved surface fixed mounting on the 2 top cambered surfaces of skirt, and seted up interval even intercommunicating pore 202 on the skirt 2 between the spoiler 201, equal fixed mounting has fixed ear seat 203 in both ends and middle part position department about the 2 bottom cambered surfaces of skirt, and stagger in proper order about three fixed ear seat 203, equal perpendicular spiro union has fixing bolt 204 in the fixed ear seat 203, blade main part 1 is at rotatory in-process, can make the cold air of entering dams and can be to the edge guide, thereby improve cooling efficiency.
Wherein, the vane body 1 includes vane trailing edge gib block 101 and air film hole 102, the even fixed mounting in outer surface interval has the blade trailing edge gib block 101 of evagination in the tail end border department of vane body 1, the even air film hole 102 in interval has vertically been seted up in the vane body 1, its air film hole 102 is linked together vane body 1 root and top, after cold air got into from blade tenon root 3, cold air partly flows along vane body 1, partly enters into the air film hole 102 of vane body 1, spray and cool off the vane leading edge through the air film that produces with air film overflow effect, and the cold air that passes through blade trailing edge gib block 101 can cool off the blade back cheek district of vane body 1, so that reach quick refrigerated purpose.
Wherein, blade tenon root 3 includes tenon 301 and drainage plate 302, and the lower extreme border department fixed mounting of blade tenon root 3 has the tenon 301 of T type form, and the left end position department of 3 front end cambered surface walls of blade tenon root and rear end cambered surface walls fixed mounting respectively has cambered surface form drainage plate 302, and the interior concave surface of drainage plate 302 is right, accessible tenon 301 is in the same place each blade group dress, and drainage plate 302 then can guide the cold air that gets into and remove to the assigned direction.
The main body of the skirt base 2 is an inclined plane structure with a high left end and a low right end, and the skirt base 2 is an arc surface structure with a forward concave surface, so that an inclined section profile can be formed in the rotating process, and the air flow can be guided to move conveniently.
Wherein, the mass flow ratio of the jet flow between the guide strips 101 at the tail edge of the blade is 1.14-6.4, and the Reynolds coefficient of the jet flow is 8000-48000, so that the cooling effect can be ensured to be in the best state.
Wherein, the rotational twist angle of the blade body 1 is sixty degrees, which is convenient for ensuring the heat conduction to be performed in an efficient state.
The specific use mode and function of the embodiment are as follows:
in the use process, the edge of the tail end of the blade body 1 is uniformly and fixedly provided with convex blade tail edge guide strips 101 at intervals along the outer surface, the blade body 1 is vertically provided with air film holes 102 at even intervals, the air film holes 102 communicate the root part and the top part of the blade body 1, when cold air enters from the blade tenon root part 3, a part of the cold air flows along the blade body 1, a part of the cold air enters into the air film holes 102 of the blade body 1, the front edge of the blade is cooled by the generated air film spraying and air film overflow effect, the cold air passing through the blade tail edge guide strips 101 can cool the blade back cheek area of the blade body 1, so as to achieve the purpose of quick cooling, in addition, four spoilers 201 at even intervals are fixedly arranged on the cambered surface at the top part of the skirt base 2 along the curved surface, the skirt bases 2 between the spoilers 201 are provided with the communication holes 202 at even intervals, both ends and the equal fixed mounting in middle part position department have fixed ear seat 203 about the 2 bottom arcs of skirt, and phase in proper order is wrong about three fixed ear seat 203, equal perpendicular spiro union has fixing bolt 204 in the fixed ear seat 203, blade main part 1 is at rotatory in-process, can make the cold air of entering cut off and can be to the edge guide, thereby improve cooling efficiency, and the lower extreme border department fixed mounting of blade tenon root 3 has tenon 301 of T type form, and the left end position department of 3 front end cambered surface walls of blade tenon root and rear end cambered surface walls fixed mounting respectively has cambered surface's drainage plate 302, the interior concave surface of drainage plate 302 is right, accessible tenon 301 is in the same place each blade group dress, and drainage plate 302 then can guide the cold air that gets into to the direction removal.
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 (7)
1. Can guarantee high-temperature alloy blade for engine of blade leading edge high-efficient cooling, its characterized in that: comprises a blade body (1); the root of the blade main body (1) is fixedly provided with a blade tenon root (3); the left side and the right side of the joint of the blade tenon root (3) and the blade main body (1) are respectively and fixedly provided with an arc-shaped skirt (2), and the blade main body (1) is inserted between the skirt (2); the skirt (2) comprises spoilers (201) and communicating holes (202), four spoilers (201) with uniform intervals are fixedly mounted on the arc surface at the top of the skirt (2) along the curved surface, and the communicating holes (202) with uniform intervals are formed in the skirt (2) between the spoilers (201).
2. A superalloy blade for an engine capable of ensuring efficient cooling of the leading edge of the blade as in claim 1, wherein: the blade body (1) comprises a blade trailing edge guide strip (101) and an air film hole (102), the outer convex blade trailing edge guide strip (101) is uniformly and fixedly installed at the tail end edge of the blade body (1) along the outer surface at intervals, the air film hole (102) with uniform intervals is vertically formed in the blade body (1), and the root and the top of the blade body (1) are communicated with the air film hole (102).
3. A superalloy blade for an engine capable of ensuring efficient cooling of the leading edge of the blade as in claim 1, wherein: skirt (2) still include fixed ear seat (203) and fixing bolt (204), both ends and the equal fixed mounting in middle part position department have fixed ear seat (203) about skirt (2) bottom cambered surface, and stagger in proper order about three fixed ear seat (203), and equal spiro union has fixing bolt (204) perpendicularly in fixed ear seat (203).
4. A superalloy blade for an engine capable of ensuring efficient cooling of the leading edge of the blade as in claim 1, wherein: blade tenon root (3) are including tenon (301) and drainage plate (302), the lower extreme border department fixed mounting of blade tenon root (3) has tenon (301) of T type form, and the left end position department of blade tenon root (3) front end cambered surface wall and rear end cambered surface wall respectively fixed mounting have cambered surface form drainage plate (302), and the interior concave surface of drainage plate (302) is right.
5. A superalloy blade for an engine capable of ensuring efficient cooling of the leading edge of the blade as in claim 1, wherein: the main body of the skirt (2) is of an inclined plane structure with a high left end and a low right end, and the skirt (2) is of an arc surface structure with a forward concave surface.
6. A superalloy blade for an engine capable of ensuring efficient cooling of the leading edge of the blade as in claim 1, wherein: the mass flow ratio of the jet flow between the guide strips (101) at the tail edge of the blade is 1.14-6.4, and the Reynolds coefficient of the jet flow is 8000-48000.
7. A superalloy blade for an engine capable of ensuring efficient cooling of the leading edge of the blade as in claim 1, wherein: the rotation twist angle of the blade main body (1) is sixty degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011386035.5A CN112648018A (en) | 2020-12-01 | 2020-12-01 | High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011386035.5A CN112648018A (en) | 2020-12-01 | 2020-12-01 | High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade |
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| Publication Number | Publication Date |
|---|---|
| CN112648018A true CN112648018A (en) | 2021-04-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011386035.5A Pending CN112648018A (en) | 2020-12-01 | 2020-12-01 | High-temperature alloy blade for engine capable of ensuring efficient cooling of front edge of blade |
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| CN (1) | CN112648018A (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001107701A (en) * | 1999-10-08 | 2001-04-17 | Mitsubishi Heavy Ind Ltd | Gas turbine moving blade |
| CN101004140A (en) * | 2003-02-05 | 2007-07-25 | 联合工艺公司 | Microcircuit cooling for a turbine blade tip |
| US20080118367A1 (en) * | 2006-11-21 | 2008-05-22 | Siemens Power Generation, Inc. | Cooling of turbine blade suction tip rail |
| CN101233298A (en) * | 2005-07-25 | 2008-07-30 | 西门子公司 | Cooling turbine blades for gas turbines and use of such turbine blades |
| CN102943693A (en) * | 2012-11-29 | 2013-02-27 | 哈尔滨汽轮机厂有限责任公司 | Efficient cooling turbine movable vane of gas turbine with low-heat and medium-heat values |
| CN103075200A (en) * | 2011-10-26 | 2013-05-01 | 通用电气公司 | Turbine bucket angel wing features for forward cavity flow control and related method |
| CN104379873A (en) * | 2012-06-15 | 2015-02-25 | 通用电气公司 | Turbine airfoil with cast platform cooling circuit |
| CN106014488A (en) * | 2016-07-07 | 2016-10-12 | 周丽玲 | Gas turbine blade with longitudinal intersection rib cooling structure |
| CN209040894U (en) * | 2018-11-28 | 2019-06-28 | 西安中捷飞工贸有限责任公司 | A kind of aero engine turbine blades with refrigerating function |
| CN111927562A (en) * | 2020-07-16 | 2020-11-13 | 中国航发湖南动力机械研究所 | Turbine rotor blade and aircraft engine |
-
2020
- 2020-12-01 CN CN202011386035.5A patent/CN112648018A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001107701A (en) * | 1999-10-08 | 2001-04-17 | Mitsubishi Heavy Ind Ltd | Gas turbine moving blade |
| CN101004140A (en) * | 2003-02-05 | 2007-07-25 | 联合工艺公司 | Microcircuit cooling for a turbine blade tip |
| CN101233298A (en) * | 2005-07-25 | 2008-07-30 | 西门子公司 | Cooling turbine blades for gas turbines and use of such turbine blades |
| US20080118367A1 (en) * | 2006-11-21 | 2008-05-22 | Siemens Power Generation, Inc. | Cooling of turbine blade suction tip rail |
| CN103075200A (en) * | 2011-10-26 | 2013-05-01 | 通用电气公司 | Turbine bucket angel wing features for forward cavity flow control and related method |
| CN104379873A (en) * | 2012-06-15 | 2015-02-25 | 通用电气公司 | Turbine airfoil with cast platform cooling circuit |
| CN102943693A (en) * | 2012-11-29 | 2013-02-27 | 哈尔滨汽轮机厂有限责任公司 | Efficient cooling turbine movable vane of gas turbine with low-heat and medium-heat values |
| CN106014488A (en) * | 2016-07-07 | 2016-10-12 | 周丽玲 | Gas turbine blade with longitudinal intersection rib cooling structure |
| CN209040894U (en) * | 2018-11-28 | 2019-06-28 | 西安中捷飞工贸有限责任公司 | A kind of aero engine turbine blades with refrigerating function |
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Application publication date: 20210413 |
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