CN210289845U - Channel type cooling air guide device for air supply of turbine movable blades - Google Patents
Channel type cooling air guide device for air supply of turbine movable blades Download PDFInfo
- Publication number
- CN210289845U CN210289845U CN201920834482.9U CN201920834482U CN210289845U CN 210289845 U CN210289845 U CN 210289845U CN 201920834482 U CN201920834482 U CN 201920834482U CN 210289845 U CN210289845 U CN 210289845U
- Authority
- CN
- China
- Prior art keywords
- guide
- wall
- ring
- air inlet
- air
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Abstract
The utility model provides a channel formula cooling air guider for turbine movable vane air feed, it relates to gas turbine auxiliary component field, and it is complicated mainly in order to solve current turbine air conditioning device framework, and the cost is higher, to the poor problem of cooling performance of blade surface and end wall, the utility model discloses a connected mode sets up a connecting pin in every through-hole and every pin joint hole in for one number, and each connecting pin respectively with a through-hole in with a pin joint hole interference fit, be equipped with the guide ring on the inner wall of a guide ring go-between, and guide ring and a guide ring go-between an organic whole set up, a connecting wall and No. two connecting wall fixed connection, No. two guide ring go-between outer walls closely laminate with the lower surface of guide ring, the utility model discloses mainly used cools off the turbine movable vane.
Description
Technical Field
The utility model relates to a gas turbine auxiliary component field, in particular to channel formula cooling air guider for turbine movable vane air feed.
Background
Gas turbines are favored by various countries since their birth due to their high power density and rapid response. Modern advanced gas turbines are rapidly developing towards the trends of high power, high efficiency, low fuel consumption, high stability and long service life, and in order to improve output power and thermal efficiency, the inlet temperature of the turbine is continuously increased, reaches 1600 ℃ level and far exceeds the temperature limit of the used materials. Efficient and highly reliable turbine cooling designs are important guarantees for gas turbine operating economy, safety and functionality. In order to improve the performance index of the gas turbine, efficient cooling technology needs to be researched to ensure the normal operation of the high-temperature components of the gas turbine. These high temperature components that require efficient cooling typically include: turbine blades, discs, etc. Turbine blade cooling techniques are divided into internal cooling and external cooling. The internal cooling mainly comprises: rib turbulence, pin rib array channels, impingement jet cooling; external cooling is primarily film cooling. In addition to this there are new composite cooling structures.
The turbine rotor blades are subjected to not only a great mechanical load but also a great thermal load during operation. The cooling structure design of the movable blade not only needs to meet the temperature requirement of metal materials, but also needs to meet the strength requirement caused by centrifugal force. The cooling means commonly used at present include air film, internal convection. An efficient energy-saving engine (E3) provided by GE company mainly comprises a front edge air film, a blade top air film and an internal two-way serpentine channel. The channels are internally provided with structures such as rough ribs, turbulence ribs, flow guiding devices and the like. The inside of the movable blade is subjected to convection cooling, the outer surface is subjected to local film cooling through holes distributed in a front edge spray header shape and holes of a blade tip pressure surface, no film cooling hole is formed in the pressure surface and the suction surface of the blade profile, and cooling airflow enters the movable blade from three root passages. The forward channel provides approximately 25% of the total bucket cooling flow for cooling the leading edge and blade tip. The flows are discharged through a series of shower-head-shaped holes with the diameter of 0.38-0.5 mm at the front edge and a row of holes with the diameter of 0.5-0.63 mm at the tip. Since the temperatures expected at the high tips of the blades are actually lower, the leading edge cooling hole layout needs to be tailored to this temperature requirement. In addition, to increase the thermal conductivity, the broken strip is designed as one piece with the inner channel. The middle section uses about two thirds of the total cold air flow of the movable vane, and the air flow circulates through the inner cavity, flows back and forth twice along the vane height, enters the tail edge channel, bypasses a row of struts and is discharged into the main flow. To improve the heat transfer coefficient, disconnected strips are used in the channels. To reduce flow separation and attendant pressure losses at the tip and root sections, guide vanes are used. The size of the flow area must be carefully selected in order to avoid creating an expanded area that may cause flow separation and large pressure losses. The third channel of the bucket distributes only a small portion of the cooling air to cool the root section area and the trailing edge. The jet of air improves the distribution of the air flow at the root turn, in particular without reducing the cold air supply pressure.
Obviously, the cooling of the turbine blades directly affects the overall performance and reliability, and therefore, the guiding device for supplying cooling air to the turbine blades is an important component of the internal cooling structure of the gas turbine. In the turbine cooling air system, the pressure loss of cooling air delivered from the stationary casing to the rotating turbine disk is large, so that the temperature of the cooling air outlet of the rotating turbine disk is increased, thereby reducing the cooling performance of cooling air on the blade surface and the end wall. The cold air guide device can reduce the relative speed of the cold air and the rotating turbine disk, reduce the flow loss of the cold air, and therefore can reduce the temperature of the cold air at the outlet of the rotating turbine disk. At present, relatively few researches on cooling air guiding devices are conducted at home and abroad, and people hope to provide a cooling air guiding device which is relatively simple in structure, relatively low in cost and high in realizability.
SUMMERY OF THE UTILITY MODEL
The utility model provides a channel type cooling air guiding device for supplying air to turbine moving blades, which aims to solve the problems of complex structure, higher cost and poor cooling performance of the surface and the end wall of the blade of the existing turbine air conditioning device;
a channel type cooling air guide device for supplying air to turbine movable blades comprises an air inlet shell, a support ring, an internal guide shell, a guide ring and N connecting pins;
the air inlet shell is in a hollow round table shape, N support ring connecting tables are arranged on the outer wall close to the large opening end of the air inlet shell at equal intervals along the circumferential direction, N is a positive integer, one end, far away from the air inlet shell, of each support ring connecting table is provided with a pin connecting hole, a guide ring connecting ring is arranged at the connecting position of each support ring connecting table and the air inlet shell, the guide ring connecting ring is arranged on the inner wall of the air inlet shell, the middle part of the outer wall of the air inlet shell is provided with M horizontal air inlet through holes at equal intervals along the circumferential direction, M is a positive integer, a connecting wall is fixedly connected to the inner wall of the air inlet shell close to each horizontal air inlet through hole, the connecting wall is arranged between the small opening end of the air inlet shell and each horizontal air inlet through hole, and the N support ring connecting tables, the air inlet;
the outer wall of the support ring is circumferentially provided with N first through holes;
the outer wall of one end of the inner guide shell is provided with a second guide ring connecting ring, the inner wall of the other end of the inner guide shell is provided with a second connecting wall, and the inner guide shell, the second guide ring connecting ring and the second connecting wall are integrally arranged;
a plurality of guide sheets are milled on the inner surface of the guide ring along the circumferential direction, and a gap between every two adjacent guide sheets is a guide channel;
set up a connecting pin in every through-hole and every pin joint hole, and every connecting pin respectively with in a through-hole and a pin joint hole interference fit, be equipped with the guide ring on the inner wall of a guide ring go-between, and guide ring and a guide ring go-between an organic whole set up, a connection wall and No. two connection wall fixed connection, No. two guide ring go-between outer walls closely laminate with the lower surface of guide ring.
The utility model discloses with prior art have following beneficial effect:
the utility model discloses on make full use of turbine director and rim plate structure space's basis, combine turbine structure and movable vane air feed characteristics, be used for the cooling air guider of turbine movable vane air feed with channel formula runner structure to through channel height and exit angle in the adjustment guide ring, obtain satisfying air feed flow and air feed angle requirement, and simple structure's cooling air guider structure. Solves the problems of large power consumption, long cold air flow and relatively complex structure of the traditional wheel disc supercharging air supply, provides a relatively simple structure of a cooling air guide device for cooling the turbine movable blades of the gas turbine,
drawings
FIG. 1 is a schematic view of a bucket cooling air guide assembly in general configuration and flow path;
FIG. 2 is a schematic view of a cooling air guide;
FIG. 3 is a cross-sectional view of the support ring;
FIG. 4 is a cross-sectional view of the support ring M-M;
FIG. 5 is a cross-sectional view of the air intake housing;
FIG. 6 is a cross-sectional view taken along line A-A of the air intake housing;
FIG. 7 is a cross-sectional view of the guide ring;
FIG. 8 is a cross-sectional view of the inner guide housing;
FIG. 9 is a side view of the air intake housing;
fig. 10 is a partially enlarged view of the guide ring.
In the figure, 1 turbine wheel disc, 2 guide vanes, 3 air inlet shells, 3-1 support ring connecting tables, 3-2 air inlet through holes, 3-3 first guide ring connecting rings, 3-4 second connecting walls, 3-5 connecting holes, 3-6 first connecting walls, 4 support rings, 4-1 first through holes, 4-2 threaded connecting holes, 4-3 guide vane connecting walls, 4-3-1 guide vane connecting grooves, 5 guide device chambers, 6 inner guide shells, 6-1 second guide ring connecting rings, 6-2 turbine wheel disc sealing walls, 6-3 second connecting walls, 7 connecting pins, 8 guide rings, 8-1 guide grooves, 8-2 guide vanes and 9 turbine movable vanes.
Detailed Description
The first embodiment is as follows: the present embodiment is described with reference to fig. 1 to 8, and the channel type cooling air guide device for turbine blade air supply in the present embodiment includes an air intake housing 3, a support ring 4, an inner guide housing 6, a guide ring 8, and N connection pins 7;
the air inlet shell 3 is in a hollow round table shape, N support ring connecting platforms 3-1 are arranged on the outer wall close to the large opening end of the air inlet shell 3 at equal intervals along the circumferential direction, N is a positive integer, one end of each support ring connecting platform 3-1 far away from the air inlet shell 3 is provided with a pin connecting hole, the connecting part of the support ring connecting platform 3-1 and the air inlet shell 3 is provided with a guide ring connecting ring 3-3, the guide ring connecting ring 3-3 is arranged on the inner wall of the air inlet shell 3, the middle part of the outer wall of the air inlet shell 3 is provided with M horizontal air inlet through holes 3-2 at equal intervals along the circumferential direction, M is a positive integer, the inner wall of the air inlet shell 3 close to each horizontal air inlet through hole 3-2 is fixedly connected with a connecting wall 3-6, and the connecting wall 3-6 is arranged between the small opening end of the air inlet shell 3 and each, the N support ring connecting tables 3-1, the air inlet shell 3, the first guide ring connecting table 3-3 and the first connecting wall 3-6 are integrally arranged;
the outer wall of the support ring 4 is circumferentially provided with N first through holes 4-1;
a second guide ring connecting ring 6-1 is arranged on the outer wall of one end of the inner guide shell 6, a second connecting wall 6-3 is arranged on the inner wall of the other end of the inner guide shell 6, and the inner guide shell 6, the second guide ring connecting ring 6-1 and the second connecting wall 6-3 are integrally arranged;
the inner surface of the guide ring 8 is milled and processed with a plurality of guide sheets 8-2 along the circumferential direction, and a gap between every two adjacent guide sheets 8-2 is a guide channel 8-1;
a connecting pin 7 is arranged in each first through hole 4-1 and each first pin connecting hole, each connecting pin 7 is in interference fit with one first through hole 4-1 and one first pin connecting hole respectively, a guide ring 8 is arranged on the inner wall of the first guide ring connecting ring 3-3, the guide ring 8 and the first guide ring connecting ring 3-3 are arranged integrally, the first connecting wall 3-6 is fixedly connected with the second connecting wall 6-3, and the outer wall of the second guide ring connecting ring 6-1 is tightly attached to the lower surface of the guide ring 8.
The utility model discloses well guide ring 8 is through milling process, the clearance between two adjacent guide vanes 8-2 constitutes cooling air flow through's guide channel 8-1, guide channel 8-1 is the passageway that contracts along the cooling air flow path, the cavity that produces when air inlet housing 3 and inside guide housing 6 rigid coupling is guider's cavity 5, guider's cavity 5 mainly is to accomodate the compressor export that enters from air inlet through-hole 3-2 and supplies the cooling air to the stator, and make these cold air pass through guide channel 8-1 and provide the cooling for turbine movable vane 9, and need carry out the wind-tunnel blowing test to the good cooling air guider of combination before the device is implemented, survey its export air current angle and air mass flow test, if export angle does not satisfy the design requirement, then the export angle of guide channel 8-1 in the adjustment (again process the angle of the opposite face of two adjacent guide vanes 8-2, thereby changing the outlet angle of the guide channel 8-1), if the outlet flow does not meet the design requirement, adjusting the aperture size and the number of the air inlet through holes 3-2 until the requirement is met, the essence of the blowing test is to inject air flow into the air inlet through holes 3-2, observe the air flow direction at the air outlet, and observe whether the optimal cooling effect can be achieved for the turbine movable blades 9.
The second embodiment is as follows: the present embodiment is described with reference to fig. 1 and 2, in which the first connecting wall 3-6 and the second connecting wall 6-3 are fixedly connected by welding, and other components and connection manners are the same as those of the first embodiment.
With the arrangement, welding is one of the most common fixing modes, the cost is low, and the fixing effect is good.
The third concrete implementation mode: referring to fig. 5, the present embodiment is described, in which a second connecting wall 3-4 is further disposed on the inner wall of the small opening end of the air inlet casing 3, and the second connecting wall 3-4 is integrally disposed with the air inlet casing 3, and other components and connecting manners are the same as those of the second embodiment.
This is provided in order to allow a better connection of the air intake housing 3 to other components of the gas turbine.
The fourth concrete implementation mode: referring to fig. 5, the present embodiment is described, in which P connection holes 3-5 are equidistantly formed in the second connection wall 3-4 along the circumferential direction, P is a positive integer, and other components and connection manners are the same as those of the third embodiment.
So set up, be convenient for admit air casing 3 and gas turbine other part pass through threaded connection, be convenient for better equipment, dismantlement and subsequent maintenance.
The fifth concrete implementation mode: the present embodiment is described with reference to fig. 1 to 3, in the present embodiment, a guide vane connecting wall 4-3 is further provided on an end surface of the support ring 4 away from the air intake housing (3), and the support ring 4 and the guide vane connecting wall 4-3 are integrally provided, and other components and connection manners are the same as those of the fourth embodiment.
The sixth specific implementation mode: the present embodiment is described with reference to fig. 1 to 3, in which a guide vane connecting groove 4-3-1 is provided on a side wall of the guide vane connecting wall 4-3 close to the support ring 4. The other components and the connection mode are the same as the fifth embodiment mode.
So set up, be convenient for support ring 4 and stator 2 are connected.
The seventh embodiment: the embodiment is described with reference to fig. 4, in the embodiment, N threaded connection holes 4-2 are further formed in the end surface of the support ring 4 along the circumferential direction, each threaded connection hole 4-2 is staggered with one first through hole 4-1, and other components and connection modes are the same as those in the sixth embodiment.
So set up, be convenient for fix cooling air guider on stator 2 through the bolt.
The specific implementation mode is eight: referring to fig. 8, the embodiment is described, in which the inner guide shell 6 and the second guide ring connecting ring 6-1 are provided with a turbine disk sealing wall 6-2, the turbine disk sealing wall 6-2 is provided with a honeycomb seal, and the inner guide shell 6 and the turbine disk sealing wall 6-2 are integrally provided. The other components and the connection mode are the same as those of the seventh embodiment.
In this way, the inner guide casing 6 and the turbine disk below the turbine rotor blades 9 form a sealing structure, cooling air leakage is reduced, and in order to be matched with the use of the turbine disk sealing wall 6-2, the turbine disk sealing wall connected with the turbine disk below the turbine rotor blades 9 can be arranged on the outer wall of the upper portion of the air inlet casing 3 in the same way, so that the sealing effect can be better.
The specific implementation method nine: the embodiment is described with reference to fig. 2 and 7, in the embodiment, the outlet angle of each guide channel 8-1 formed between two adjacent guide blades 8-2 is a, the value range of a is 10 to 12 °, the depth of the guide channel 8-1 is H, the value range of H is 40 to 60mm, and other components and connection modes are the same as those in the eighth embodiment.
The detailed implementation mode is ten: the present embodiment is described with reference to fig. 1 to 3, in the present embodiment, the value range of N in the N support ring connecting platforms 3-1 is 35 to 45, the value range of M in the M air inlet through holes 3-2 is 75 to 85, the aperture of the air inlet through hole 3-2 is R, the value range of R is 40 to 60mm, and other components and connecting manners are the same as those in the ninth embodiment.
Principle of operation
Firstly, connect air inlet housing 3, support ring 4, inside guide housing 6, guide ring 8 and N connecting pins 7 through embodiment one the relation of connection, connect into cooling air guider, and the cooling air guider who will connect links together through support ring 4 and stator 2, through turbine rim plate sealed wall 6-2 and turbine rim plate 1 sealing connection (if also set up turbine rim plate sealed wall on air inlet housing 3, then air inlet housing 3 also needs sealing connection with turbine rim plate 1, if do not set up turbine rim plate sealed wall on air inlet housing 3, then air inlet housing 3 and turbine rim plate welded fastening), constitute the air feed channel formula cooling air guider of complete turbine movable blade air feed.
The channel type cooling air guide device for supplying air to the assembled turbine rotor blades is shown as an air flow path shown by an arrow in fig. 1, cooling air at the outlet of a compressor of a gas turbine is introduced into a chamber 5 of the guide device through an air inlet through hole 3-2 of an air inlet shell 3 and flows out through guide rings 8 shown in fig. 5, the cooling air changes the flowing direction after passing through the guide channel 8-1 between the guide rings 8, is supplied to the turbine wheel disc 1 along the air flow path shown in fig. 1 and is supplied to the turbine rotor blades 9 through holes in the turbine wheel disc 1 to provide cooling air for the turbine rotor blades 9.
Claims (10)
1. A channeled cooling air guide for turbine bucket air supply, characterized by: the air inlet device comprises an air inlet shell (3), a support ring (4), an internal guide shell (6), a guide ring (8) and N connecting pins (7);
the air inlet shell (3) is in a hollow round table shape, N support ring connecting platforms (3-1) are arranged on the outer wall close to the large opening end of the air inlet shell (3) at equal intervals along the circumferential direction, N is a positive integer, one end, far away from the air inlet shell (3), of each support ring connecting platform (3-1) is provided with one pin connecting hole, the connecting position of each support ring connecting platform (3-1) and the air inlet shell (3) is provided with one guide ring connecting ring (3-3), the one guide ring connecting ring (3-3) is arranged on the inner wall of the air inlet shell (3), the middle part of the outer wall of the air inlet shell (3) is provided with M horizontal air inlet through holes (3-2) at equal intervals along the circumferential direction, M is a positive integer, one connecting wall (3-6) is fixedly connected on the inner wall of the air inlet shell (3) close to each horizontal air inlet through hole (3-2), and the one connecting wall (3-6) is arranged at the small opening N support ring connecting platforms (3-1), the air inlet shell (3), a first guide ring connecting platform (3-3) and a first connecting wall (3-6) are integrally arranged among the air through holes (3-2);
the outer wall of the support ring (4) is provided with N first through holes (4-1) along the circumferential direction;
a second guide ring connecting ring (6-1) is arranged on the outer wall of one end of the inner guide shell (6), a second connecting wall (6-3) is arranged on the inner wall of the other end of the inner guide shell (6), and the inner guide shell (6), the second guide ring connecting ring (6-1) and the second connecting wall (6-3) are integrally arranged;
a plurality of guide sheets (8-2) are milled on the inner surface of the guide ring (8) along the circumferential direction, and a gap between every two adjacent guide sheets (8-2) is a guide channel (8-1);
a connecting pin (7) is arranged in each first through hole (4-1) and each first pin connecting hole, each connecting pin (7) is in interference fit with one first through hole (4-1) and one first pin connecting hole respectively, a guide ring (8) is arranged on the inner wall of the first guide ring connecting ring (3-3), the guide ring (8) and the first guide ring connecting ring (3-3) are arranged integrally, the first connecting wall (3-6) is fixedly connected with the second connecting wall (6-3), and the outer wall of the second guide ring connecting ring (6-1) is tightly attached to the lower surface of the guide ring (8).
2. The channeled cooling air guide device for turbine blade air supply of claim 1, wherein: the first connecting wall (3-6) and the second connecting wall (6-3) are fixedly connected by welding.
3. The channeled cooling air guide device for turbine blade air supply of claim 1, wherein: the inner wall of the small opening end of the air inlet shell (3) is also provided with a second connecting wall (3-4), and the second connecting wall (3-4) and the air inlet shell (3) are integrally arranged.
4. The channeled cooling air guide device for turbine blade air supply of claim 3, wherein: p connecting holes (3-5) are arranged on the second connecting wall (3-4) at equal intervals along the circumferential direction, and P is a positive integer.
5. The channeled cooling air guide device for turbine blade air supply of claim 1, wherein: the end face, far away from the air inlet shell (3), of the support ring (4) is further provided with a guide vane connecting wall (4-3), and the support ring (4) and the guide vane connecting wall (4-3) are integrally arranged.
6. The channeled cooling air guide device for turbine blade air supply of claim 5, wherein: the guide vane connecting wall (4-3) is provided with a guide vane connecting groove (4-3-1) on the side wall close to the support ring (4).
7. The channeled cooling air guide device for turbine blade air supply of claim 6, wherein: n threaded connection holes (4-2) are further formed in the end face of the support ring (4) along the circumferential direction, and each threaded connection hole (4-2) and one through hole (4-1) are arranged in a staggered mode.
8. The channeled cooling air guide device for turbine blade air supply of claim 1, wherein: the inner guide shell (6) and the second guide ring connecting ring (6-1) are provided with a turbine wheel disc sealing ring (6-2), a honeycomb sealing piece is installed on the turbine wheel disc sealing ring (6-2), and the inner guide shell (6) and the turbine wheel disc sealing ring (6-2) are integrally arranged.
9. The channeled cooling air guide device for turbine blade air supply of claim 1, wherein: the outlet angle of each guide channel (8-1) formed between two adjacent guide sheets (8-2) is a, the value range of a is 10-12 degrees, the depth of each guide channel (8-1) is H, and the value range of H is 40-60 mm.
10. The channeled cooling air guide device for turbine blade air supply of claim 1, wherein: the value range of N in the N support ring connecting tables (3-1) is 35-45, the value range of M in the M air inlet through holes (3-2) is 75-85, the aperture of the air inlet through holes (3-2) is R, and the value range of R is 40-60 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920834482.9U CN210289845U (en) | 2019-06-04 | 2019-06-04 | Channel type cooling air guide device for air supply of turbine movable blades |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920834482.9U CN210289845U (en) | 2019-06-04 | 2019-06-04 | Channel type cooling air guide device for air supply of turbine movable blades |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210289845U true CN210289845U (en) | 2020-04-10 |
Family
ID=70072257
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920834482.9U Active CN210289845U (en) | 2019-06-04 | 2019-06-04 | Channel type cooling air guide device for air supply of turbine movable blades |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210289845U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110206591A (en) * | 2019-06-04 | 2019-09-06 | 中国船舶重工集团公司第七0三研究所 | A kind of groove-type cooling air guiding device for turbine rotor blade gas supply |
| CN112539086A (en) * | 2020-10-27 | 2021-03-23 | 哈尔滨广瀚燃气轮机有限公司 | Sectional rotary supercharging device for cooling air of turbine rotor blade |
-
2019
- 2019-06-04 CN CN201920834482.9U patent/CN210289845U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110206591A (en) * | 2019-06-04 | 2019-09-06 | 中国船舶重工集团公司第七0三研究所 | A kind of groove-type cooling air guiding device for turbine rotor blade gas supply |
| CN112539086A (en) * | 2020-10-27 | 2021-03-23 | 哈尔滨广瀚燃气轮机有限公司 | Sectional rotary supercharging device for cooling air of turbine rotor blade |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8523527B2 (en) | Apparatus for cooling a platform of a turbine component | |
| CA2485179C (en) | Split flow turbine nozzle | |
| US8753083B2 (en) | Curved cooling passages for a turbine component | |
| US5634766A (en) | Turbine stator vane segments having combined air and steam cooling circuits | |
| CA2809000C (en) | Dual-use of cooling air for turbine vane and method | |
| US8870525B2 (en) | Bucket assembly for turbine system | |
| EP1221538A2 (en) | Cooled turbine stator blade | |
| CN104420887B (en) | A kind of turbine of gas turbine | |
| JP2017198205A (en) | Airfoil for turbine engine | |
| US10830057B2 (en) | Airfoil with tip rail cooling | |
| CN108884716B (en) | Turbine airfoil with internal cooling passage having flow splitter feature | |
| JPH02233802A (en) | Cooling type turbine blade | |
| CN110206591A (en) | A kind of groove-type cooling air guiding device for turbine rotor blade gas supply | |
| CN210289845U (en) | Channel type cooling air guide device for air supply of turbine movable blades | |
| EP3415719B1 (en) | Turbomachine blade cooling structure | |
| US20170234225A1 (en) | Component cooling for a gas turbine engine | |
| CN203403909U (en) | Turbine body of gas turbine | |
| US10830082B2 (en) | Systems including rotor blade tips and circumferentially grooved shrouds | |
| CN111350549B (en) | Cooling structure suitable for be rich in and fire working medium turbine high temperature quiet leaf | |
| JP5331743B2 (en) | Gas turbine blade | |
| EP1361337A1 (en) | Turbine airfoil cooling configuration | |
| CN220226985U (en) | Blade for gas turbine | |
| CN213039331U (en) | Turbine rotor blade for a gas turbine engine | |
| CN117489418B (en) | Turbine guide vane and cold air guide piece of front cold air cavity thereof | |
| KR102599918B1 (en) | turbine vane and turbine including the same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |