CN208380634U - A kind of big riblet is alternately cooled the gas turbine blade of structure - Google Patents
A kind of big riblet is alternately cooled the gas turbine blade of structure Download PDFInfo
- Publication number
- CN208380634U CN208380634U CN201820456819.2U CN201820456819U CN208380634U CN 208380634 U CN208380634 U CN 208380634U CN 201820456819 U CN201820456819 U CN 201820456819U CN 208380634 U CN208380634 U CN 208380634U
- Authority
- CN
- China
- Prior art keywords
- rib
- flow
- blade
- partition
- big
- 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
Abstract
The utility model discloses gas turbine blades that a kind of big riblet is alternately cooled structure, including blade, blade root platform, internal cooling cavity room, forced-convection heat transfer fin and leaf top gas film cooling hole etc.；Along the transverse direction for strengthening heat convection circuit, one longitudinal intersection fin is at least set；Flow-disturbing rib is size alternant.Cooling structure described in the utility model changes vortex structures inside cooling duct, improves blade heat transfer coefficient, reduces runner frictional resistant coefficient, improves the cooling blade heat transfer characteristic of turbine, extends blade service life.
Description
Technical field
The utility model relates to a kind of gas turbines, and in particular to a kind of big riblet is alternately cooled the combustion gas turbine leaf of structure
Piece.
Background technique
Leading edge mostly uses impact-gaseous film control, the design of blade high-performance fin and leaf when turbine cooling structure designs at present
The flow-disturbing rib of column of piece trailing edge designs.The rotating channel cooling structure of blade occupies extremely important in the current turbine type of cooling
Status is a kind of typical high effect forced heat convection technology.Cooling air-flow swing flow inside blade cavity, extends gas
Stream is in the residence time of internal cooling chamber, and under the effect of the flow-disturbing of pressure surface side and suction surface side rib piece, generation outmatches master
Secondary Flow on stream enhances the turbulivity of mainstream to achieve the purpose that enhanced heat exchange.
Utility model content
The purpose of the utility model is to provide the gas turbine blade that a kind of big riblet is alternately cooled structure, the combustion gas turbines
Blade, which is effectively broken, is attached to inner flow passage wall surface thermal boundary layer, improves cooling gas utilization rate, reduces and hinders along Cheng Liudong
Power, and gas turbine blade surface thermal load is reduced, and the application of big riblet can make inner passage have better heat transfer effect
And smaller flow resistance coefficient.
In order to achieve the above objectives, what the utility model adopts the following technical solution to realize:
A kind of big riblet is alternately cooled the gas turbine blade of structure, blade and blade root platform including integrated molding,
Blade is internally provided with cooling chamber, cooling chamber enclosed by the pressure face and suction surface and leading edge and trailing edge of blade set and
At, and several leading edge film cooling holes are offered in leading edge, several trailing edge ventholes, the top of blade are offered on trailing edge
It is provided with top plate, if offering cured leaf top gas film cooling hole on top plate, is offered at the center of blade root platform and cooling chamber's phase
The air inlet of connection；
It is connected between the inner surface of blade pressure face and the inner surface of suction surface by the partition that several longitudinal gaps are arranged,
And the first partition at cooling chamber center is set, the air inlet at blade root platform center is divided into two parts；It is arranged in cooling
Partition one end at left and right sides of first partition at chamber center is connected with blade root platform, and the other end is extension end or one end
It is connected with top plate, the other end is extension end, and the partition being connected with blade root platform and the baffle interval being connected with top plate setting；
The inner surface and suction surface of blade pressure face between two neighboring partition and between rightmost side partition and trailing edge
Inner surface on be provided with the flow-disturbing ribs of several parallel arrangements, passed through between flow-disturbing rib by longitudinally disposed longitudinal intersection rib
It wears, flow-disturbing rib is arranged alternately using size fin, and the small fin height of flow-disturbing rib is 0.3~0.5 times of big fin height.
The utility model, which further improves, to be, be arranged on the left of the first partition at cooling chamber center be followed successively by with
The connected second partition of blade root platform, the third partition being connected with top plate and with blade root platform and top plate be connected the 4th every
Plate, and several impact openings are offered on the 4th partition；Be arranged on the right side of the first partition at cooling chamber center be followed successively by with
The 6th partition the 5th connected partition of blade root platform and be connected with top plate.
The utility model, which further improves, to be, at trailing edge by longitudinal gap be arranged several turbulence columns formed it is several
Trailing edge venthole.
The utility model, which further improves, to be, one is at least offered in each turbulence columns for exchange above and below air-flow
Venthole.
The utility model, which further improves, to be, flow-disturbing rib is oblique rib, V-arrangement rib or separate type V-arrangement rib.
The utility model, which further improves, to be, longitudinal rib that intersects at least is arranged on the flow-disturbing rib of several parallel arrangements
One, and each longitudinal direction intersection rib extends to the last item from first flow-disturbing rib on the flow-disturbing rib of several parallel arrangements and disturbs
Flow rib.
The utility model, which further improves, to be, flow-disturbing rib is the fin for having certain angle with air current flow direction,
The range of the angle is 30 °~45 °.
The utility model, which further improves, to be, the cross section of flow-disturbing rib is square.
The utility model, which further improves, to be, the small fin of flow-disturbing rib is located at the big rib in big fin streamwise downstream
At 0.5~0.75 distance of piece spacing.
The utility model, which further improves, to be, flow-disturbing rib and longitudinal intersection rib pass through casting and forming.
The utility model has the advantage that
The longitudinal intersection rib of blade cooling chamber arrangement intersected with flow-disturbing rib, longitudinal intersection rib changes cooling in channel
The vortex structures of air-flow destroy the thermal boundary layer that cooling air-flow flowing generates, increase turbulivity in channel, strengthen turbine interior and change
Heat effectively improves cooling gas utilization rate, reduces blade surface thermic load, has the turbo blade preferable whole cooling
Performance.Flow-disturbing rib is alternately arranged structure using big riblet simultaneously, can reduce flow resistance, and the structure is relatively easy, has
Good processability.
Therefore, the utility model is realized passive control to cooling air-flow, is reduced by changing original channel flow-disturbing rib structure
Turbine blade surface temperature improves blade service life.
Detailed description of the invention
Fig. 1 is the longitdinal cross-section diagram of the utility model gas turbine blade；
Fig. 2 a is a kind of size flow-disturbing rib and longitudinal intersection rib arrangement form of the utility model turbine blade, longitudinal to intersect
Rib runs through from the middle part of oblique rib；
Fig. 2 b is a kind of size flow-disturbing rib and longitudinal intersection rib arrangement form of the utility model turbine blade, longitudinal to intersect
Rib runs through from the middle part angle of V-arrangement rib；
Fig. 2 c is a kind of size flow-disturbing rib and longitudinal intersection rib arrangement form of the utility model turbine blade, longitudinal to intersect
Rib runs through from the midline of separate type V-arrangement rib；
Fig. 2 d is a kind of size flow-disturbing rib and longitudinal intersection rib arrangement form of the utility model turbine blade, two longitudinal directions
Intersection rib is evenly arranged on oblique rib passage；
Fig. 2 e is a kind of size flow-disturbing rib and longitudinal intersection rib arrangement form of the utility model turbine blade, two longitudinal directions
Intersection rib is evenly arranged on the midline of two column V-arrangement ribs.
Specific embodiment
The utility model is further described in detail with reference to the accompanying drawing:
As shown in Figure 1, a kind of big riblet of the utility model is alternately cooled the gas turbine blade of structure, including integrated chemical conversion
The blade 1 and blade root platform 2 of type, blade 1 are internally provided with cooling chamber 3, pressure face and suction of the cooling chamber 3 by blade 1
Power face and leading edge 4 and trailing edge 5 are enclosed and are set, and several leading edge film cooling holes 401 are offered in leading edge 4, in trailing edge 5
On offer several trailing edge ventholes 501, the top of blade 1 is provided with top plate 6, if it is cold to offer cured leaf top gas film on top plate 6
But hole 601 offer at the center of blade root platform 2 and the air inlet that is connected；
The partition phase being arranged between the inner surface of 1 pressure face of blade and the inner surface of suction surface by several longitudinal gaps
Even, and the first partition 9 at 3 center of cooling chamber is set, the air inlet at 2 center of blade root platform is divided into two parts；Setting
Partition one end of the left and right sides of first partition 9 at 3 center of cooling chamber is connected the other end with blade root platform 2 for extension end,
Or one end is connected the other end with top plate 6 for extension end, and the partition being connected with blade root platform 2 and the partition being connected with top plate 6
Interval setting；
The inner surface and suction of 1 pressure face of blade between two neighboring partition and between rightmost side partition and trailing edge 5
It is provided with the flow-disturbing rib 7 of several parallel arrangements on the inner surface in face, and passes through longitudinal direction between the flow-disturbing rib 7 of several parallel arrangements
Longitudinal intersection rib 8 of setting runs through.Wherein, flow-disturbing rib 7 and longitudinal intersection rib 8 are rectangular fins.Preferably, flow-disturbing rib 7 is
Oblique rib, V-arrangement rib or separate type V-arrangement rib.Preferably, flow-disturbing rib 7 is the fin for having certain angle with air current flow direction, should
The range of angle is 30 °~45 °.
Preferably, longitudinal intersection rib 8 at least arranges one, and each longitudinal direction on the flow-disturbing rib 7 of several parallel arrangements
Intersection rib 8 extends to the last item flow-disturbing rib 7 from first flow-disturbing rib 7 on the flow-disturbing rib 7 of several parallel arrangements.
Wherein, it is arranged on the left of the first partition 9 at 3 center of cooling chamber and is followed successively by second to be connected with blade root platform 2
Partition 10, the third partition 11 being connected with top plate 6 and the 4th partition 12 being connected with blade root platform 2 and top plate 6, and
Several impact openings 121 are offered on four partitions 12；It is arranged on the right side of the first partition 9 at 3 center of cooling chamber and is followed successively by and leaf
The 6th partition 14 the 5th connected partition 13 of root platform 2 and be connected with top plate 6.
Preferably, several trailing edge ventholes 501 are formed by several turbulence columns 15 that longitudinal gap is arranged at trailing edge 5, and
The venthole 151 exchanged up and down for air-flow is at least offered in each turbulence columns 15.
In order to further understand the utility model, an explanation now is done to its working principle.
Cooling chamber 3 provided by the utility model is rotating channel, and cooling air-flow enters from 2 bottom air inlet of blade root platform
Blade 1, respectively forwardly edge 4 and the flowing of 5 direction of trailing edge, the air-flow that forward edge 4 flows are disturbed by three fins after intermediate bulkhead
Leading edge impinging cooling chamber is sprayed into after flowing chamber, leading edge film cooling holes 401 is passed through and enters mainstream combustion gas formation air film, cover leaf
Piece obstructs high-temperature fuel gas；The air-flow flowed to tail source 5 crosses three fin flow-disturbing chambers, flows through the turbulence columns 15 at trailing edge 5, from
Trailing edge venthole 501 enters mainstream combustion gas.It is provided in the turbulence columns 15 of blade trailing edge 5 and exchanges the logical of flowing up and down for air-flow
On the one hand stomata 151 increases the heat exchange area of cooling air-flow, on the other hand reduces gas-flow resistance.The flow-disturbing of blade body
Rib 7 and air current flow direction are disposed in each channel interior top-down with flow-disturbing rib phase at 30 °~45 ° angles
Longitudinal intersection rib 8 of friendship, longitudinal height for intersecting rib 8 are identical as flow-disturbing rib big in flow-disturbing rib.Turbine cools down blade, cooling duct
Longitudinally intersection rib 8 enhances cooling air-flow turbulivity later for interior addition, weakens thermal boundary layer to the adhesion of blade inner wall, improves
Turbine blade cooling performance.Flow-disturbing rib can reduce the on-way resistance of cooling air-flow using size flow-disturbing rib combining form, keep
Higher pressure, while improving the channel wall coefficient of heat transfer.
The utility model is added longitudinal can induce in the channel after rib and generates new whirlpool, is distributed in the two sides of rib,
Involving velocity is generated to the thermal boundary on channel surface, turbulent flow in channel can be further increased with the superposition between stylish generation whirlpool
Degree plays the role of enhanced heat exchange to blade, and big riblet is used alternatingly reduction along journey gas-flow resistance, keeps cooling air-flow pressure,
Benign effect is further functioned as to cooling effect.
The longitudinal intersection rib and size flow-disturbing rib flow-disturbing rib that the utility model is proposed are integrated casting and forming, structure letter
It is single, it is easy to process.
It is only a kind of form of involved internal structure given by attached drawing 1, before being intended to without departing from the utility model
It puts, can also there is other and longitudinal flow-disturbing rib structure for intersecting rib intersection, Fig. 2 a-2e gives suitable the utility model aim
A variety of flow-disturbing rib structures.Fig. 2 a flow-disturbing rib structure is oblique rib, and Fig. 2 b is V-arrangement rib, and Fig. 2 c is separate type V-arrangement rib, Fig. 2 d and figure
2e is along the multiple longitudinal intersection ribs of single cooling chamber setting.
Specific implementation case described in the utility model is only several cases that the utility model is intended to, Bu Nengyong
The scope of the utility model is limited, all falls within the guarantor of the utility model according to other equivalence changes that the utility model is done
Within the scope of shield.
Claims (8)
1. the gas turbine blade that a kind of big riblet is alternately cooled structure, which is characterized in that the blade (1) including integrated molding
With blade root platform (2), blade (1) is internally provided with cooling chamber (3), pressure face and suction of the cooling chamber (3) by blade (1)
Power face and leading edge (4) and trailing edge (5) are enclosed and are set, and several leading edge film cooling holes (401) are offered on leading edge (4),
Several trailing edge ventholes (501) are offered on trailing edge (5), are provided with top plate (6) at the top of blade (1), top plate opens up on (6)
If there is cured leaf top gas film cooling hole (601), the air inlet being connected with cooling chamber (3) is offered at the center of blade root platform (2)
Mouthful；
It is connected between the inner surface of blade (1) pressure face and the inner surface of suction surface by the partition that several longitudinal gaps are arranged,
And the air inlet at blade root platform (2) center is divided into two parts by the first partition (9) being arranged at cooling chamber (3) center；
Partition one end at left and right sides of the first partition (9) at cooling chamber (3) center is arranged to be connected with blade root platform (2), it is another
End is that extension end or one end are connected with top plate (6), and the other end is extension end, and the partition that is connected with blade root platform (2) and with
The connected baffle interval setting of top plate (6)；
The inner surface and suction of blade (1) pressure face between two neighboring partition and between rightmost side partition and trailing edge (5)
It is provided with the flow-disturbing rib (7) of several parallel arrangements on the inner surface in face, passes through longitudinally disposed longitudinal phase between flow-disturbing rib (7)
Rib (8) are handed over to run through, flow-disturbing rib (7) is arranged alternately using size fin, and the small fin height of flow-disturbing rib (7) is big fin height
0.3~0.5 times；
Flow-disturbing rib (7) is oblique rib, V-arrangement rib or separate type V-arrangement rib；The small fin of flow-disturbing rib (7) is located at big fin along flowing side
Downstream at 0.5~0.75 distance of big fin spacing, and the small fin of flow-disturbing rib (7) and big fin integrally casting shaping.
2. the gas turbine blade that a kind of big riblet according to claim 1 is alternately cooled structure, which is characterized in that setting
Be followed successively by the left of first partition (9) at cooling chamber (3) center the second partition (10) being connected with blade root platform (2) and
The 4th partition (12) top plate (6) connected third partition (11) and be connected with blade root platform (2) and top plate (6), and
Several impact openings (121) are offered on 4th partition (12)；On the right side of the first partition (9) being arranged at cooling chamber (3) center
It is followed successively by the 5th partition (13) being connected with blade root platform (2) and the 6th partition (14) being connected with top plate (6).
3. the gas turbine blade that a kind of big riblet according to claim 1 or 2 is alternately cooled structure, which is characterized in that
Several trailing edge ventholes (501) are formed by several turbulence columns (15) that longitudinal gap is arranged at trailing edge (5).
4. the gas turbine blade that a kind of big riblet according to claim 3 is alternately cooled structure, which is characterized in that each
The venthole (151) exchanged up and down for air-flow is at least offered in turbulence columns (15).
5. the gas turbine blade that a kind of big riblet according to claim 1 is alternately cooled structure, which is characterized in that longitudinal
Intersection rib (8) at least arranges one on the flow-disturbing rib (7) of several parallel arrangements, and each longitudinally intersects rib (8) several
The last item flow-disturbing rib (7) is extended to from first flow-disturbing rib (7) on the flow-disturbing rib (7) of parallel arrangement.
6. the gas turbine blade that a kind of big riblet according to claim 1 is alternately cooled structure, which is characterized in that flow-disturbing
Rib (7) is the fin for having certain angle with air current flow direction, and the range of the angle is 30 °~45 °.
7. the gas turbine blade that a kind of big riblet according to claim 1 is alternately cooled structure, which is characterized in that flow-disturbing
The cross section of rib (7) is square.
8. the gas turbine blade that a kind of big riblet according to claim 1 is alternately cooled structure, which is characterized in that flow-disturbing
Rib (7) and longitudinal intersection rib (8) pass through casting and forming.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820456819.2U CN208380634U (en) | 2018-04-02 | 2018-04-02 | A kind of big riblet is alternately cooled the gas turbine blade of structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820456819.2U CN208380634U (en) | 2018-04-02 | 2018-04-02 | A kind of big riblet is alternately cooled the gas turbine blade of structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208380634U true CN208380634U (en) | 2019-01-15 |
Family
ID=64975047
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820456819.2U Active CN208380634U (en) | 2018-04-02 | 2018-04-02 | A kind of big riblet is alternately cooled the gas turbine blade of structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208380634U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110410158A (en) * | 2019-08-16 | 2019-11-05 | 杭州汽轮动力集团有限公司 | A kind of turbine rotor blade of gas turbine |
| CN110501135A (en) * | 2019-08-22 | 2019-11-26 | 西安交通大学 | Become Mach number molded line wind-tunnel high temperature jet pipe wall array type enhanced heat exchange cooling structure |
| CN111648830A (en) * | 2020-05-14 | 2020-09-11 | 西安交通大学 | Internal cooling ribbed channel for rear part of turbine moving blade |
-
2018
- 2018-04-02 CN CN201820456819.2U patent/CN208380634U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110410158A (en) * | 2019-08-16 | 2019-11-05 | 杭州汽轮动力集团有限公司 | A kind of turbine rotor blade of gas turbine |
| CN110410158B (en) * | 2019-08-16 | 2022-04-12 | 杭州汽轮动力集团有限公司 | Turbine rotor blade of gas turbine |
| CN110501135A (en) * | 2019-08-22 | 2019-11-26 | 西安交通大学 | Become Mach number molded line wind-tunnel high temperature jet pipe wall array type enhanced heat exchange cooling structure |
| CN111648830A (en) * | 2020-05-14 | 2020-09-11 | 西安交通大学 | Internal cooling ribbed channel for rear part of turbine moving blade |
| CN111648830B (en) * | 2020-05-14 | 2021-04-20 | 西安交通大学 | Internal cooling ribbed channel for rear part of turbine moving blade |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104791020B (en) | A kind of have the gas turbine blade longitudinally intersecting rib cooling structure | |
| CN208380634U (en) | A kind of big riblet is alternately cooled the gas turbine blade of structure | |
| CN106168143B (en) | A kind of turbine blade trailing edge cooling structure with lateral pumping groove and ball-and-socket | |
| CN211715181U (en) | Laminate cooling structure with slotted circular turbulence column | |
| CN103089335A (en) | W-shaped rib channel cooling structure suitable for turbine blade backside cooling cavity | |
| CN112746871B (en) | Continuous wave rib cooling structure with trapezoidal cross section | |
| JPH0370084B2 (en) | ||
| CN103437889B (en) | A kind of branch's film hole structure for gas turbine engine cooling | |
| CN107060892B (en) | A kind of turbine blade cooling unit of gas-liquid coupling | |
| CN112177681B (en) | Fractal intermittent rib structure suitable for internal cooling of turbine blade | |
| CN105874168A (en) | Gas turbine engine component comprising a trailing edge cooling using angled impingement on surface enhanced with cast chevron arrangements | |
| CN104594956B (en) | A kind of structure improving fluting air film hole downstream wall gas film cooling efficiency | |
| CN210396821U (en) | Marine gas turbine high pressure turbine stator cooling structure | |
| CN204609950U (en) | A kind of have the gas turbine blade longitudinally intersecting rib cooling structure | |
| CN108757047A (en) | Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column | |
| CN114109514B (en) | Turbine blade pressure surface cooling structure | |
| CN114109515B (en) | Turbine blade suction side cooling structure | |
| CN113513372B (en) | Double-wall turbine guide blade with small air guiding amount | |
| CN215633158U (en) | Turbine cooling blade of gas turbine | |
| CN111271133A (en) | Turbine guider blade with complex fin structure inner cooling channel | |
| CN106640213A (en) | Lateral air film wall cooling structure for turbine blade | |
| CN112746872B (en) | Through continuous folded plate structure suitable for tail edge part of turbine blade | |
| CN113605992A (en) | Gas turbine cooling blade with internal micro-channels | |
| CN114198155A (en) | Cooling structure | |
| CN113719323A (en) | Composite cooling structure for turbine blade of gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |