CN101100951A - Gradually widened slot staggered rib passage suitable for internal cooling member as turbine blade - Google Patents
Gradually widened slot staggered rib passage suitable for internal cooling member as turbine blade Download PDFInfo
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- CN101100951A CN101100951A CNA200710118766XA CN200710118766A CN101100951A CN 101100951 A CN101100951 A CN 101100951A CN A200710118766X A CNA200710118766X A CN A200710118766XA CN 200710118766 A CN200710118766 A CN 200710118766A CN 101100951 A CN101100951 A CN 101100951A
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Abstract
This invention is a turbine blade internal cooling structure. This cooling structure is a notched crossed-rib channel, which groove width increases gradually along from channel inlet to outlet. For the crossed-rib channel that is long along the flow direction, the inner fluid flow resistance will decrease when both sides of channel have micro pass way with the best width. Thus, the heat exchanging ability of inter-fluid will increase. This invention realizes the optimizing design of turbine blade cooling structure.
Description
Technical field
The present invention is a kind of cooling structure that is applicable to cold parts in the turbine blade etc., and this cooling structure is to slot to central direction in the two side walls of staggered rib passage, and the width of fluting increases gradually along feeder connection to Way out, forms gradually wide apleuria conduit.
Background technique
Turbine blade in gas turbine engine is close to the firing chamber, and its ambient temperature of living in part is up to 2000K.In order to improve the thermal efficiency of gas turbine engine, the general employing improved turbine inlet temperature, and what bring is the increase of turbine part heat load thereupon.In addition, turbine blade (working blade) is in the middle of the very high centrifugal field work under the high rotating speed (changeing more than the scooter 15000rpm).In bad working environment like this, guarantee the work that blade is normal, reliable, long-term, just must effectively cool off turbine blade, keep best thermal stress state.The principle of cooling is to use minimum air conditioning quantity to guarantee the blade reliably working.Turbine cooling blade in using at present has a variety of, wherein be with the Russia representative be the compound staggered rib of multi-cavity cooling channel.Staggered rib on its passage is generally staggered rib (seeing also shown in Figure 1).Its structural parameter one have 7, are respectively channel width W, the channel height H, the passage length L that describe channel design, and rib height e, rib width t, rib spacing p and the rib angle of inclination beta of describing rib structure.Its structure is seen Fig. 3, Fig. 4, Fig. 5.In case these parameters determine that then staggered rib passage can uniquely be determined.When the high e=H/2 of rib, two row fins contact up and down, and this moment, whole passage was divided into many little grids (7) by fin, and this is a kind of special shape in the staggered rib passage, also is called grid passage (Latticework Channel) simultaneously.Jiao Cuo fin forms many subaisles (6) up and down, after cooling blast flows into the grid passage, to flow along each subaisle (6), the deflection of 2 β then can take place when flowing to channel side wall, and then constantly turnover in passage, so increased the mobile distance of cooled gas in passage, and owing at the sidewall air-flow big turnover takes place, the secondary flow of formation can heat exchanging play humidification.Fig. 2 has provided the mobility status of staggered rib passage inner air.Moreover because passage is divided into a lot of little grids (7), blending will certainly take place in air-flow between each grid (7) except flowing according to above-mentioned rule, and the irregular secondary flow of Xing Chenging also helps to destroy overlay like this, strengthens the heat exchange effect.In addition, a large amount of fins has also increased the heat exchange area in the passage, and this heat exchange effect for channel interior also plays a part positive.
As seen the cooling of this structure makes the blade good cooling results, and thermal force is little, uniformity of temperature profile, and thermal stress is little.But the deficiency of this structure is also very obviously bigger as the pressure loss, the not high shortcoming of cold air utilization ratio.
Summary of the invention
The purpose of this invention is to provide a kind of cooling structure that is applicable to cold parts in the turbine blade etc., what this cooling structure was emphasized is the structural type that groove width is increased to outlet gradually by channel entrance in slot staggered rib passage, with the optimum optimization everywhere of mobile in the realization passage and heat exchange effect.
At staggered rib passage heat exchange strong advantage and the big shortcoming of flow resistance, studies show that the smooth passage (3) (5) of opening apleuria in the passage both sides (sees Fig. 6,7 and 10) can reduce the stream group greatly, have a fluid flow channel (3) (5) between diagonal rib (2) and the tunnel ends wall (8) this moment, because also can effluent fluid in the smooth passage of both sides simultaneously around here fluid can and subaisle (6) (see figure 7) inner fluid produce interaction, and select to strengthen when suitable heat exchange in the passage at channel width w, this measure can strengthen the General of passage greatly, and structure is seen Fig. 6, Fig. 8, Fig. 9, Figure 10 and Figure 11.But, discover that the groove width w of streamwise the best is cumulative, structure is seen Fig. 5--7.So in order to obtain optimum comprehensive heat exchange and flow effect, optimum cooling structure is designed to conduit (3) longshore current to gradually wide.
The present invention is used for the staggered rib cooling structure in inside of turbine blade intermediate portion and trailing edge, the cooling chamber of the wide W of high H cooling channel is that β and-two groups of β staggered ribs (2) are separated into a plurality of little secondary fluid channels (6) by the wide t of high e tilt angle, wherein e is half of H, the both sides, cooling channel have apleuria conduit (5), its new feature of the present invention is: the both sides, cooling channel have the gradually wide apleuria conduit (3) of longshore current body flow direction, along channel entrance (1) to the slot staggered rib passage that increases gradually of outlet (2) direction groove width, the ratio w/W of the conduit width w of inlet part (1) and staggered rib passage width W is between 0.75/70 to 1.25/70, longshore current is to the linear increase of this value, to outlet port (4) w/W value is between 2/70 to 4/70, locate get 0.75/70 to 1.0/70 smaller value to length L/W greater than 1.0 staggered rib passage import (1) for longshore current, the value that outlet (4) is located gets 3/70 to 4/70, locates get 1.0/70 to 1.27/70 higher value to length L/W less than 1.0 staggered rib passage import (1) for longshore current, the value that outlet (4) is located gets 2/70 to 3/70.
The invention has the advantages that: 1) the passage both sides have all had the conduit of apleuria, changed the structural type that traditional staggered rib passage inner fluid flows, and have played the effect that forced heat exchanging reduces flow resistance; 2) longshore current body flow direction, the smooth well width w of apleuria everywhere is the numerical value that can realize local optimum cooling effect, realizes the inner cooling structure of high efficiency turbine blade; 3) passage heat exchange uniformity is everywhere further optimized, and helps reducing the thermal stress of turbine blade.
Description of drawings
Fig. 1 staggered rib passage structural representation
Fig. 2 staggered rib passage internal flow situation schematic representation
The half of staggered rib passage structural representation of Fig. 3
Fig. 4 staggered rib passage parametric representation 1
Fig. 5 staggered rib passage parametric representation 2
Fluting road, Fig. 6 staggered rib passage both sides schematic representation
The sectional structure chart of the gradually wide type conduit of Fig. 7 slot staggered rib passage
The entity structure 1 of the gradually wide type conduit of Fig. 8 slot staggered rib passage
The entity structure 2 of the gradually wide type conduit of Fig. 9 slot staggered rib passage
Figure 10 heads straight for the sectional structure chart of groove staggered rib passage
The entity structure 1 of Figure 11 straight trough road slot staggered rib passage
The entity structure 2 of Figure 12 straight trough road slot staggered rib passage
Among the figure: 1, channel entrance 2, diagonal rib 3. flaring type conduits 4, groove width conduit 6. secondary streams passages 7. diagonal ribs such as channel outlet 5. form grid 8. tunnel ends wall w. conduit width P. two rib spacing t. rib width β. and rib inclination angle e. rib height L. flows to passage length H. channel height W. channel width
Embodiment
The present invention is described in further detail below in conjunction with accompanying drawing.
The present invention is the conclusion that gets through simplified model experiment and its heat exchange of Study on Three Dimensional Numerical Simulation and flow resistance characteristic, this rule of finding when the researchs of experiment and numerical value are headed straight for the heat exchange of groove (5) staggered rib passage and flow resistance characteristic with the variation relation of groove width w.Result of study shows that the resistance coefficient along with the increase passage of groove width w reduces always.Fluting makes the increase of channel for heat exchange effect mainly concentrate on preceding half section that fluid flows, different groove width w to the passage second half section to influence difference little.Therefore, can consider that preceding half section at passage is chosen heat exchange effect pairing groove width w preferably time the, smaller value.The passage second half section can suitably increase groove width w under few situation that heat exchange efficiency reduces, help reducing the flow resistance of passage like this.
Etc. groove width w slot staggered rib passage (as Fig. 8--shown in 11).For the unslotted staggered rib passage, cooling air flows in passage (6), locates air-flow at tunnel ends wall (8) and can turn back and enter in the next subaisle (6).Split conduit (5) staggered rib passage, cooling air flowing in passage (6), in the subaisle that links to each other that is confined to turn back to, can not pass through conduit (5) yet and directly flow out, can turn back in other the subaisle (6) yet by conduit (5), mobility status is more various, the increasing that influences each other of flowing between the subaisle (6) makes the mobile than complicated more before the fluting of two side walls zone, helps energy in time to transport away, strengthened convection heat exchange, flow resistance reduces to some extent simultaneously.But the comprehensive heat exchange efficiency of this structure is not best.
After further improving, slot staggered rib passage (as Fig. 5--shown in 7), promptly from channel entrance (1) to the conduit (3) that increases gradually of outlet (4) groove width w, along channel entrance (1) to the slot staggered rib passage that increases gradually of outlet (4) direction groove width, the ratio w/W of its conduit width w of inlet part and staggered rib passage width W is between 0.75/70 to 1.25/70, longshore current is to the linear increase of this value, to outlet port w/W value is between 2/70 to 4/70, get smaller value for longshore current to the bigger staggered rib passage inlet of length, the value in outlet port is got higher value, gets higher value for longshore current to the less staggered rib passage inlet of length, the value in outlet port is got smaller value.Flow resistance has obtained maximum reduction in the passage, and is about 40 percent, particularly the passage streamwise by the rear section; Exchange capability of heat obtains the first mate and improves, and is about 20 percent, particularly the channel entrance part.The present invention makes the overall thermal stress distribution more even from the thermal conduction study angle, and also far below the cooled blade of former staggered rib, comprehensive heat exchange and mobile index improve more than 30 percent the pressure loss.
Claims (2)
1, a kind of staggered rib cooling structure in inside that is used for high-pressure turbine blade intermediate portion and trailing edge, the cooling chamber of the wide W of high H cooling channel is that β and-two groups of β staggered ribs (2) are separated into a plurality of little secondary fluid channels (6) by the wide t of high e tilt angle, wherein e is half of H, the both sides, cooling channel have apleuria conduit (5), its new feature of the present invention is: the both sides, cooling channel have the gradually wide apleuria conduit (3) of longshore current body flow direction, between diagonal rib (2) in the passage and the passage end wall segment distance w is arranged, along channel entrance (1) to the slot staggered rib passage that increases gradually of outlet (2) direction groove width, the ratio w/W of the conduit width w of inlet part (1) and staggered rib passage width W is between 0.75/70 to 1.25/70, longshore current is between 2/70 to 4/70 to the linear increase of this value to outlet port (4) w/W value.
2, cooling structure according to claim 1, wherein: for longshore current to length L/W greater than 1.0 staggered rib, the value that channel entrance (1) locates to get 0.75/70 to 1.0/70, outlet (4) is located gets 3/70 to 4/70, for longshore current to length L/W less than 1.0 staggered rib, the value that channel entrance (1) locates to get 1.0/70 to 1.27/70, outlet (4) is located gets 2/70 to 3/70.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200710118766XA CN100557199C (en) | 2007-07-13 | 2007-07-13 | A kind ofly be applicable to the gradually wide type slot staggered rib passage in the cold parts in the turbine blade etc. |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200710118766XA CN100557199C (en) | 2007-07-13 | 2007-07-13 | A kind ofly be applicable to the gradually wide type slot staggered rib passage in the cold parts in the turbine blade etc. |
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| Publication Number | Publication Date |
|---|---|
| CN101100951A true CN101100951A (en) | 2008-01-09 |
| CN100557199C CN100557199C (en) | 2009-11-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNB200710118766XA Expired - Fee Related CN100557199C (en) | 2007-07-13 | 2007-07-13 | A kind ofly be applicable to the gradually wide type slot staggered rib passage in the cold parts in the turbine blade etc. |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104100380A (en) * | 2014-07-02 | 2014-10-15 | 北京航空航天大学 | Heat exchange method of mainstream gas of aero-engine |
| CN106761948A (en) * | 2016-11-28 | 2017-05-31 | 西北工业大学 | A kind of depression rib structure for turbine blade internal cooling passage |
| CN108548435A (en) * | 2018-06-08 | 2018-09-18 | 陕西益信伟创智能科技有限公司 | Based on bionical linear ribs row's type small staggeredly alveolar heat exchanger core body and heat exchanger |
| CN108548436A (en) * | 2018-06-08 | 2018-09-18 | 陕西益信伟创智能科技有限公司 | Based on bionical dot matrix small staggeredly alveolar heat exchanger core body and heat exchanger |
| CN108759524A (en) * | 2018-06-08 | 2018-11-06 | 陕西益信伟创智能科技有限公司 | Based on bionical curvilinear ribs row's type small staggeredly alveolar heat exchanger core body and heat exchanger |
| CN110337530A (en) * | 2017-03-10 | 2019-10-15 | 川崎重工业株式会社 | The cooling structure of turbo blade |
| CN110418873A (en) * | 2017-03-10 | 2019-11-05 | 川崎重工业株式会社 | The cooling structure of turbo blade |
| CN110714802A (en) * | 2019-11-28 | 2020-01-21 | 哈尔滨工程大学 | Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade |
| 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 |
| CN112145235A (en) * | 2020-09-24 | 2020-12-29 | 大连理工大学 | Omega type gyration chamber plywood cooling structure |
| CN113374535A (en) * | 2021-06-28 | 2021-09-10 | 常州大学 | Lattice array type double-layer cooling gas turbine blade |
| CN113483362A (en) * | 2021-08-18 | 2021-10-08 | 中国联合重型燃气轮机技术有限公司 | Flame tube and gas turbine |
| CN113623011A (en) * | 2021-07-13 | 2021-11-09 | 哈尔滨工业大学 | Turbine blade |
| CN113623010A (en) * | 2021-07-13 | 2021-11-09 | 哈尔滨工业大学 | Turbine blade |
-
2007
- 2007-07-13 CN CNB200710118766XA patent/CN100557199C/en not_active Expired - Fee Related
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104100380A (en) * | 2014-07-02 | 2014-10-15 | 北京航空航天大学 | Heat exchange method of mainstream gas of aero-engine |
| CN104100380B (en) * | 2014-07-02 | 2016-04-27 | 北京航空航天大学 | A kind of aeroengine mainstream gas heat exchange method |
| CN106761948A (en) * | 2016-11-28 | 2017-05-31 | 西北工业大学 | A kind of depression rib structure for turbine blade internal cooling passage |
| CN110337530A (en) * | 2017-03-10 | 2019-10-15 | 川崎重工业株式会社 | The cooling structure of turbo blade |
| CN110418873A (en) * | 2017-03-10 | 2019-11-05 | 川崎重工业株式会社 | The cooling structure of turbo blade |
| CN108548435A (en) * | 2018-06-08 | 2018-09-18 | 陕西益信伟创智能科技有限公司 | Based on bionical linear ribs row's type small staggeredly alveolar heat exchanger core body and heat exchanger |
| CN108548436A (en) * | 2018-06-08 | 2018-09-18 | 陕西益信伟创智能科技有限公司 | Based on bionical dot matrix small staggeredly alveolar heat exchanger core body and heat exchanger |
| CN108759524A (en) * | 2018-06-08 | 2018-11-06 | 陕西益信伟创智能科技有限公司 | Based on bionical curvilinear ribs row's type small staggeredly alveolar heat exchanger core body and heat exchanger |
| CN110714802A (en) * | 2019-11-28 | 2020-01-21 | 哈尔滨工程大学 | Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade |
| 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 |
| CN112145235A (en) * | 2020-09-24 | 2020-12-29 | 大连理工大学 | Omega type gyration chamber plywood cooling structure |
| CN113374535A (en) * | 2021-06-28 | 2021-09-10 | 常州大学 | Lattice array type double-layer cooling gas turbine blade |
| CN113623011A (en) * | 2021-07-13 | 2021-11-09 | 哈尔滨工业大学 | Turbine blade |
| CN113623010A (en) * | 2021-07-13 | 2021-11-09 | 哈尔滨工业大学 | Turbine blade |
| CN113483362A (en) * | 2021-08-18 | 2021-10-08 | 中国联合重型燃气轮机技术有限公司 | Flame tube and gas turbine |
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| Publication number | Publication date |
|---|---|
| CN100557199C (en) | 2009-11-04 |
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Granted publication date: 20091104 Termination date: 20120713 |