CN213574237U - Turbine blade internal turbulence device - Google Patents
Turbine blade internal turbulence device Download PDFInfo
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- CN213574237U CN213574237U CN202022719048.1U CN202022719048U CN213574237U CN 213574237 U CN213574237 U CN 213574237U CN 202022719048 U CN202022719048 U CN 202022719048U CN 213574237 U CN213574237 U CN 213574237U
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- turbine blade
- spoiler
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Abstract
The utility model discloses an inside vortex device of turbine blade, including the inside cooling channel wall, set up the spoiler on the wall. The spoiler consists of the integrated first subsection and the integrated second subsection which are arranged along the airflow flowing direction, and the spoiler consisting of the two subsections can improve the flowing structure of the internal cooling channel, weaken the flow loss after the spoiler and improve the wall surface heat exchange efficiency.
Description
Technical Field
The utility model relates to a gas turbine blade, concretely relates to inside vortex device of turbine blade.
Background
The spoiler enhanced heat exchange is to disturb a fully developed boundary layer through a spoiler on a wall surface, so that the thickness of a thermal boundary layer is reduced, and the convective heat exchange coefficient is increased. The turbulent flow fin is the most classical turbulent flow structure in the reinforced heat exchanger, and the fin turbulator not only increases the effective heat exchange area of the blade cooling channel, but also causes the intensive mixing of fluids in different areas in the channel, and disturbs the development of a boundary layer, thereby improving the heat exchange effect. The fins are arranged in the channel to enhance the heat exchange efficiency, but the flow resistance of the cold air is increased along with the insertion of the fins, and the development of a novel turbulence rib structure with better comprehensive cooling and flowing characteristics has important theoretical research significance and engineering application value.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an inside vortex device of turbine blade, the device have increased the effective heat transfer area of blade cooling channel, reduce the reattachment loss behind the spoiler, improve the cooling gas utilization ratio.
In order to achieve the purpose, the utility model adopts the following technical scheme to realize:
the utility model provides an inside vortex device of turbine blade, the device is used for the inside cooling channel of hollow blade of turbine, includes the inside cooling channel wall to and along the flow direction set up the spoiler on the inside cooling channel wall, the spoiler comprises the second vortex subsection of first vortex subsection and the integration that the nodical setting of integration was crossed.
The utility model discloses a further improvement lies in, and turbine hollow blade internal cooling channel arranges a set ofly at least the spoiler.
The utility model discloses a further improvement lies in, the first vortex subsection and the second vortex subsection of spoiler are along the central plane A-A symmetric distribution of spoiler on the spoiler cross section.
The utility model is further improved in that the included angle alpha between the first turbulence subsection and the wall surface of the internal cooling channel along the flow direction is 30-150 degrees.
The further improvement of the present invention is that the angle alpha between the second turbulence element and the inner cooling channel wall is between 30 deg. and 150 deg..
The utility model discloses a further improvement lies in, the first vortex subsection and the second vortex subsection of spoiler are less than 180 near the contained angle beta of spoiler top on the spoiler cross section.
The utility model discloses a further improvement lies in, on the spoiler cross section, the first vortex subsection and the second vortex subsection intersect the point position of spoiler and set up to: H/H is more than or equal to 0.3 and less than 1, H is the height of the cross section intersection position, and H is the height of the spoiler in the vertical direction of the wall surface.
The utility model discloses a further improvement lies in, the width L of cross section is greater than the height H of spoiler along the wall vertical direction.
The utility model discloses at least, following profitable technological effect has:
the utility model provides a pair of inside vortex device of turbine blade through changing original passageway vortex rib structure, realizes passive control to the cooling air flow, reduces turbine blade surface temperature, has improved blade life.
Drawings
FIG. 1 is a schematic view of a turbine blade turning rib channel;
FIG. 2 is a schematic cross-sectional parameter view of a turbine blade internal turbulator in accordance with the present invention;
FIG. 3a is a structural view of a turbulator for a turbine blade internal turbulator according to the present invention, where α is a right angle;
FIG. 3b shows a turbulator configuration of a turbine blade internal turbulator according to the present invention, where α is an obtuse angle;
FIG. 3c is a schematic view of a turbulator configuration within a turbine blade according to the present invention, where α is an acute angle;
FIG. 3d is a schematic view of a turbulator configuration within a turbine blade according to the present invention, where α is a right angle, the upper portions of the first and second turbulator sections are rounded, and the intersection of the first and second turbulators is rounded;
FIG. 3e shows a turbine blade internal turbulator configuration of the present invention, where α is a right angle, the upper portions of the first and second turbulators are rounded, the intersection of the first and second turbulators is rounded, and the junction of the first and second turbulators and the wall surface is rounded;
FIG. 4 is a schematic view of a conventional flow perturbation structure with diagonal ribs, V-shaped ribs and W-shaped ribs for cooling channels inside a turbine blade.
Detailed Description
The invention is described in further detail below with reference to the accompanying drawings:
FIG. 1 is a classic turbine blade internal cooling turnover rib passageway schematic diagram, the utility model provides an internal vortex device of turbine blade for the internal cooling channel of turbine hollow blade arranges a set ofly at least in the internal cooling channel the spoiler, including internal cooling channel wall 1 to and set up the spoiler 2 on internal cooling channel wall 1, the spoiler comprises first vortex subsection 3 of integration and the second vortex subsection 4 of integration.
The first spoiler subsection 3 and the second spoiler subsection 4 of the spoiler 2 are symmetrically distributed along the central plane a-a of the spoiler 2 over the cross section of the spoiler 2.
The angle alpha between the first turbulence subsection 3 in the flow direction and the wall surface 1 of the internal cooling channel is between 30 and 150 degrees.
The first spoiler subsection 3 and the second spoiler subsection 4 of the spoiler 2 have an angle of less than 180 ° in the cross-section of the spoiler 2 close to above the spoiler.
On the cross section of the spoiler 2, the intersection positions of the first spoiler subsection 3 and the second spoiler subsection 4 of the spoiler 2 are set as follows: H/H is more than or equal to 0.3 and less than 1, wherein H is the height of the cross section intersection position, H is the height of the spoiler in the vertical direction of the wall surface, and L is the width of the cross section.
The turbine blade internal turbulence device and the turbine blade are manufactured through integrated forming through technologies such as precision casting and additive manufacturing. The interface of the first and second turbulence distribution portions is "concave" downwards. When the air current passes through the vortex device, the vortex structure is generated by the induction of the first vortex subsection, a new vortex structure is formed at the interface of the two parts, and then the vortex structure passes through the second vortex subsection, so that the vortex device can weaken the vortex behind the traditional vortex ribs, and the wall surface heat exchange efficiency is improved.
Fig. 2 shows only one form of the internal structure concerned, and other spoiler structures are possible without deviating from the purpose of the invention, and fig. 3a, 3b, 3c, 3d, 3e show various spoiler structures suitable for the purpose of the invention.
Wherein, fig. 3a shows a spoiler structure form of the present invention, and α is a right angle; fig. 3b shows a spoiler according to the present invention, wherein α is an obtuse angle; fig. 3c shows a structure of the permeable spoiler of the present invention, wherein α is an acute angle; fig. 3d shows a spoiler according to the present invention, where α is a right angle, the upper portions of the first and second spoiler sections are rounded, and the intersection of the first and second spoiler sections is rounded; fig. 3e shows a spoiler structure according to the present invention, where α is a right angle, the upper portions of the first and second spoiler sections are rounded, the intersection of the first and second spoiler sections is rounded, and the connection between the first and second spoiler sections and the wall surface is rounded.
Implement on the turbine blade the utility model discloses the time, can carry out radius, two parts carry out the radius on the spoiler to the junction of spoiler and wall, this is favorable to reducing gaseous flow resistance, and it is specific depending on actual blade design.
Fig. 4 shows the oblique rib, the V-shaped rib, the W-shaped rib that are common in the cooling channel inside the turbine blade, in practical implementation, the utility model provides a spoiler structure form of the turbulator inside the turbine blade is applied to the cooling channel inside the turbine blade, i.e. the oblique rib, the V-shaped rib, the W-shaped rib of the inner cooling channel have the utility model discloses a spoiler structure of two subsections, persons in this field can also think of other basic ribs have the utility model provides a spoiler structure with two subsections.
Turbine blade internal cooling passageway unilateral wall is arranged a set ofly at least along the flow direction the utility model discloses an inside vortex device spoiler of turbine blade, in other embodiments, passageway both sides face can all be arranged the utility model provides a spoiler.
When introducing elements of various embodiments of the present invention, the articles "a," "an," "the," and "said" are intended to mean that there are one or more of the elements, and that the terms "include," "include," and "have" are intended to be inclusive and mean that there may be additional elements other than the listed elements.
The specific embodiment of the present invention is only intended for several cases of the present invention, and can not be used to limit the range of the present invention, and other equivalent changes made by the present invention all fall within the protection scope of the present invention.
Claims (8)
1. The utility model provides an inside vortex device of turbine blade, its characterized in that, the device is used for the inside cooling channel of hollow blade of turbine, including inside cooling channel wall (1) to and along flow direction setting up vortex generator (2) on inside cooling channel wall (1), vortex generator (2) are constituteed by the first vortex subsection (3) that the nodical setting of integration intersects and the second vortex subsection (4) of integration.
2. A turbine blade internal turbulator device according to claim 1, wherein at least one set of said turbulators (2) is arranged in the turbine hollow blade internal cooling channels.
3. A turbine blade internal turbulator device according to claim 1, wherein the first turbulator part (3) and the second turbulator part (4) of the turbulator (2) are symmetrically distributed along the central plane a-a of the turbulator (2) over the cross-section of the turbulator (2).
4. A turbine blade internal turbulator device according to claim 1, wherein the first flow turbulence subsection (3) in the flow direction makes an angle α of 30 ° to 150 ° with the internal cooling channel wall surface (1).
5. A turbine blade internal turbulator device according to claim 1, wherein the second flow turbulence subsection (4) in the flow direction makes an angle α of 30 ° to 150 ° with the internal cooling passage wall surface (1).
6. A turbine blade internal turbulator device according to claim 1, wherein the first turbulator subsection (3) and the second turbulator subsection (4) of the turbulator (2) have an angle β of less than 180 ° in the cross-section of the turbulator (2) close above the turbulator.
7. A turbine blade internal turbulator device according to claim 1, wherein the cross section of the turbulator (2) is such that the intersection point of the first turbulator part (3) and the second turbulator part (4) of the turbulator (2) is: H/H is more than or equal to 0.3 and less than 1, H is the height of the cross section intersection position, and H is the height of the spoiler in the vertical direction of the wall surface.
8. A turbine blade internal turbulator in accordance with claim 7, wherein the width L of the cross section is larger than the height H of the turbulator in the direction perpendicular to the wall surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022719048.1U CN213574237U (en) | 2020-11-20 | 2020-11-20 | Turbine blade internal turbulence device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022719048.1U CN213574237U (en) | 2020-11-20 | 2020-11-20 | Turbine blade internal turbulence device |
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| CN213574237U true CN213574237U (en) | 2021-06-29 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115013075A (en) * | 2022-08-10 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Anti-slip pattern-shaped turbulence rib and turbine blade |
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2020
- 2020-11-20 CN CN202022719048.1U patent/CN213574237U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115013075A (en) * | 2022-08-10 | 2022-09-06 | 中国航发四川燃气涡轮研究院 | Anti-slip pattern-shaped turbulence rib and turbine blade |
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