CN111648830B - Internal cooling ribbed channel for rear part of turbine moving blade - Google Patents
Internal cooling ribbed channel for rear part of turbine moving blade Download PDFInfo
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- CN111648830B CN111648830B CN202010408311.7A CN202010408311A CN111648830B CN 111648830 B CN111648830 B CN 111648830B CN 202010408311 A CN202010408311 A CN 202010408311A CN 111648830 B CN111648830 B CN 111648830B
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- channel
- wall surface
- rib
- front wall
- ribs
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
Abstract
The invention discloses an internally cooled ribbed channel for the aft portion of a turbine bucket, comprising: a channel with a rectangular cross section, which is hollow inside and is used for fluid to flow through; the front wall surface and the rear wall surface of the rectangular cross-section channel are symmetrically provided with a plurality of inclined turbulence ribs; the inclined turbulence ribs are arranged in an inclined mode relative to the flowing direction of the fluid; the center of the front wall surface of the rectangular cross-section channel is provided with a cross rib communicated with the inclined turbulence rib of the front wall surface. Under the rotation condition, the strong heat exchange area between the inclined fins is changed from one original part to two existing parts through the crossed ribs, the coverage area is increased, the heat exchange strengthening is more uniform, in addition, secondary flows generated by the crossed rib structure and the inclined rib structure are greatly strengthened by the Coriolis force generated by rotation, the heat exchange capacity is further enhanced, secondary flow can be influenced due to the fact that the front wall surface fins and the rear wall surface fins are arranged differently, the heat exchange difference caused by rotation of the front wall surface fins and the rear wall surface fins is effectively neutralized, the thermal stress is improved, and the service life of the blade is prolonged.
Description
Technical Field
The invention belongs to the technical field of turbine blades of gas turbines, and particularly relates to an inner-cooling ribbed channel for the rear part of a turbine moving blade.
Background
Gas turbines are widely used in aviation propulsion, land power generation and other industrial equipment, and the development of turbine cooling technology plays a crucial role in improving the thermal efficiency and output power of advanced high-temperature gas turbine engines. The flow disturbing rib enhanced cooling is to generate flow separation by repeatedly arranging the flow disturbing ribs, and then to re-attach a new boundary layer to the heat transfer surface, so as to enhance heat exchange; in addition, the separated boundary layer enhances the mixing of the wall fluid and the main flow, and heat from the near wall can be more effectively transferred to the main flow, so that the heat exchange is further enhanced.
Korean meson et al first studied the heat transfer and friction coefficient distribution of ribbed channel surfaces. They found that the repeated diagonal ribs performed better than the repeated transverse ribs. In the parallel plate channel, the heat exchange enhancement effect is significantly enhanced under the same frictional resistance condition as compared with the channel with repeated 45-degree inclined ribs and repeated transverse ribs, because the inclined ribs can generate secondary flow developed along the ribs and generate a secondary flow with larger volume in the main flow area. The plane in which the secondary flow moves is perpendicular to the main flow direction with respect to the main flow. The secondary flow among the fins can increase the reattachment speed of the fluid on the basis of the separation and reattachment flow generated by the 90-degree fins, improve the transverse mass transfer of the area among the fins and improve the heat exchange of the wall surface. The secondary flow of the main flow area can bring the fluid with higher temperature in the near-wall area away from the wall surface, so that the mass transfer capacity of the whole cross section is improved, the heat transfer temperature difference of the convection heat transfer of the near-wall area is further improved, and the heat flow density is improved.
Under the rotation state, the Coriolis force and the rotation buoyancy force can change the flow and temperature distribution in the cooling channel and influence the surface heat transfer coefficient distribution. Wherein the direction of the coriolis force depends on the direction of rotation and the direction of the cooling fluid, so that the coriolis force is different in direction when the channel direction angles are different. For radially outward flow channels, coriolis forces move the primary flow toward the backwall face wall. If both the rear wall and the front wall are heated symmetrically, the rotation causes the turbulence of the rear wall (the surface referred to by coriolis force) to increase and the turbulence of the front wall (the surface away from the coriolis force) to decrease, thereby causing the heat exchange of the front wall to be weaker than that of the rear wall. Therefore, in order to improve the uniformity of heat transfer, it is necessary to reduce the difference in heat exchange between the front and rear wall surfaces.
Heeyon Chung et al studied the effect of intersecting ribs in diagonal-rib rectangular channels of different aspect ratios on heat and mass transfer performance. In the channel with the inclined ribs, the heat transfer and mass transfer performance of the channel is reduced as the width-to-height ratio of the channel is increased because the eddy current induced by the inclined ribs is reduced as the width-to-height ratio of the channel is increased. To overcome this disadvantage, a cross rib is used which bisects the oblique rib. The 60 ° diagonal rib structure was tested for heat transfer performance with and without the intersecting ribs. It follows that when there are intersecting ribs, additional vortices are generated at each point of intersection with the oblique ribs. Therefore, when the crossed rib is added to the common inclined rib structure, the heat and mass transfer performance of all channel width-to-height ratios is remarkably improved.
Disclosure of Invention
The invention aims to provide an internally-cooled ribbed channel for the rear part of a turbine movable blade, so as to improve the heat exchange difference between the front wall surface and the rear wall surface caused by Coriolis force under a rotating condition, strengthen secondary flow in the ribbed channel by utilizing the action of the Coriolis force, enhance the heat exchange capability of the channel and improve the uniformity of heat transfer distribution.
In order to achieve the purpose, the invention adopts the following technical scheme:
an internally-cooled ribbed channel for an aft portion of a turbine bucket, comprising:
a channel with a rectangular cross section, which is hollow inside and is used for fluid to flow through;
the front wall surface and the rear wall surface of the rectangular cross-section channel are symmetrically provided with a plurality of inclined turbulence ribs; the inclined turbulence ribs are arranged in an inclined mode relative to the flowing direction of the fluid;
the front wall center of the rectangular cross section channel is provided with a cross rib which is communicated with the front wall and avoids inclining turbulence ribs.
Further, the cross rib divides the front wall face of the rectangular cross-section channel into two parts.
Further, the rib direction of the inclined turbulence rib forms an obtuse angle with the direction of the Coriolis force applied to the main flow.
Further, the rib direction refers to a direction along the fins at an acute angle to the main flow direction.
Further, the coriolis force formula is that Fcor is 2m Ω × U, where Fcor is the coriolis force applied to the fluid, Ω is the channel rotation angular velocity, and U is the fluid movement velocity.
Furthermore, the width-to-height ratio W/H of the rectangular-section channel is 2-4.
Further, the inclined spoiler rib has an inclination angle β of 30 ° to 75 °.
Furthermore, the cross section of the inclined turbulence rib is square, and the rib height e1＝0.06～0.12Dh，DhThe hydraulic diameter of the channel with the rectangular section is provided, and the rib spacing P is 8-12 e1。
Furthermore, the cross section of the cross rib is rectangular or square, the length of the cross rib in the width direction is consistent with that of the inclined turbulence rib, and the length is e1Length e in the height direction2＝0.5～1e1。
Preceding wall is crossing rib structure, and the back wall is slope vortex rib structure: the distribution of the inclined turbulence ribs on the front wall surface and the rear wall surface is symmetrical; the cross fins are only arranged on the front wall surface of the channel, the front wall surface is equally divided, and the cross fins are not arranged on the rear wall surface.
Although the cross ribs and the oblique turbulence ribs are described separately, two ribs in the front wall surface intersecting rib structure are cast into a whole.
Compared with the prior art, the invention adopts the following technical scheme:
according to the internal cooling ribbed channel for the rear part of the turbine movable blade, the strong heat exchange area between the inclined ribs is changed from one original part to two existing parts through the intersecting ribs, the coverage area is increased, and the heat exchange reinforcement is more uniform. Particularly, under the rotating condition, secondary flow generated by the crossed rib structure is greatly strengthened, the heat exchange capability is further enhanced, secondary flow can be influenced by the difference of arrangement of the front wall surface fins and the rear wall surface fins, the heat exchange difference caused by rotation of the front wall surface and the rear wall surface is effectively neutralized, a good effect is achieved on improvement of thermal stress, and therefore the service life of the blade is prolonged.
Drawings
An internally-cooled ribbed passage for the aft portion of a turbine bucket according to the present invention is described in further detail below with reference to the accompanying drawings and embodiments
FIG. 1 is a schematic view of the structure of the inner cooling passage of the present invention
FIG. 2 is a schematic view showing the principle of the arrangement of the inclined spoiler ribs of the inner cooling passage of the present invention
FIG. 3 is a side view of an embodiment of the internal cooling passages of the present invention
FIG. 4 is a top view of the rear wall of an embodiment of the internal cooling passages of the present invention
FIG. 5 is a top view of the front wall of an embodiment of the internal cooling passage of the present invention
In the figure, 1: a rectangular cross-section channel; 2: inclining the turbulence ribs; 3: a cross rib; fcor: (ii) a coriolis force; omega: rotational angular velocity; u is the main flow speed; o isrib: a rib direction; α: a channel direction angle; w: the width of the channel; h: the height of the channel; e.g. of the type1: cross rib width; e.g. of the type2: the height of the crossed ribs is high; p: rib spacing; beta: the inclined ribs are inclined at an angle.
Detailed Description
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
The following detailed description is exemplary in nature and is intended to provide further details of the invention. Unless otherwise defined, all technical terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention.
Referring to FIGS. 1 and 2, the present invention provides an internally-cooled ribbed passage for the aft portion of a turbine bucket: repeated inclined turbulence ribs 2 are uniformly distributed on the front wall surface and the rear wall surface of the channel 1 with the rectangular cross section, the cross section is square, and the arrangement of the inclined turbulence ribs 2 on the front wall surface and the rear wall surface is symmetrical. Besides the function of enhancing heat exchange of the fluid on the separation wall surface, the invention adopts the main reason that the inclined turbulence ribs can enable the fluid on the separation wall surface to generate a velocity component in the width direction of the channel so as to generate secondary flow. In order to enable the coriolis force generated by the rotation to intensify, rather than attenuate, the secondary flow generated by the oblique turbulator ribs, the arrangement of the oblique turbulator ribs must follow the principle that the rib direction, which is along the fins at an acute angle to the main flow direction, makes an obtuse angle with the direction in which the main flow is subjected to the coriolis force. The coriolis force formula is that Fcor is 2m Ω × U, where Fcor is the coriolis force applied to the fluid, Ω is the angular velocity of rotation of the rectangular cross-section channel 1, and U is the fluid movement velocity.
Example 1:
in connection with FIG. 35, in the embodiment, intersecting ribs and continuous ribs are respectively arranged on two wall surfaces of a channel 1 with a rectangular cross section and the width-to-height ratio of 4: 1; the rear wall surface is only provided with inclined turbulence ribs 2, and the front wall surface is prevented from being provided with the inclined turbulence ribs 2 and crossed ribs 3; the cross section of the inclined turbulence rib 2 is square, and the cross section of the cross rib 3 is rectangular; rib height e of inclined spoiler rib 21＝0.078Dh，DhThe hydraulic diameter of the channel 1 with the rectangular section is shown, and the rib spacing P is 10 e. The cross section of the cross rib 3 is rectangular or square, the length of the cross rib in the width direction is the same as that of the inclined turbulence rib 2, and the length is e1Length e in the height direction2＝0.5e1. The cross ribs 3 equally divide the front wall surface.
With reference to fig. 2-5, in this embodiment, relative to a general 60 ° continuous rib channel, a crossed rib 3 is disposed on the front wall surface, and the front wall surface is divided into two parts, so that under a rotation condition, the fluid near the front wall surface is disturbed by the crossed rib 3 and then leaves the wall surface again to enter the main flow, and interacts with the main flow in the main flow region, so as to divide the secondary flow near the front wall surface of the channel into two parts, thereby enhancing the mixing of the fluid near the front wall surface and the main flow, increasing the heat transfer temperature difference of the convection heat exchange in the near wall surface region, and enhancing the heat exchange of the front wall surface; the intercostal secondary flow of the channel adjacent the rear wall is also split into two by the indirect influence of the flow from the front wall, and although the boundary is less pronounced near the front wall, the rear wall heat exchange is thus enhanced. Especially, the component of the Coriolis force applied to the main flow in the height direction of the channel is directed from the front wall surface to the rear wall surface, which is the root cause of the heat exchange difference between the front wall surface and the rear wall surface of the channel, but in the invention, the direction of the Coriolis force component is the same as the flow direction of the separated fluid from the front wall surface, so that the secondary flow near the front wall surface is strengthened to a certain extent; on the other hand, the component of the coriolis force in the channel width direction further enhances the secondary flow in the entire channel, with a larger magnitude of enhancement of the secondary flow near the front wall surface. In conclusion, under the rotation condition, the invention utilizes the Coriolis force generated by rotation to enhance the heat exchange of the channel integrally and simultaneously greatly reduce the heat exchange difference of the front wall surface and the rear wall surface.
Example 2: by adopting the invention, beta is 60 DEG, e2＝e1＝0.078DhThe channel direction angle is 45 degrees, the rotation number is 0.15, and the comparison numerical calculation is carried out under the rotation condition that the Reynolds number is 10000: the average Knoop number ratio (0.986) of the front wall surface and the rear wall surface of the invention is improved by 4 percent compared with the inclined rib channel (0.949) and is improved by 10 percent compared with the common crossed rib channel (0.896). In addition, the heat exchange capacity of the invention is between the inclined rib channel and the common intersecting rib channel which are arranged by the same arrangement method as the invention, the arrangement modes of the inclined ribs in the three channels are the same, the heat exchange capacity is enhanced under the rotation condition, but the heat exchange uniformity of the front wall surface and the rear wall surface of the inclined rib channel and the intersecting rib channel is poorer, especially the heat exchange uniformity of the front wall surface and the rear wall surface of the common intersecting rib channel is seriously deteriorated under the rotation condition, so the invention is suitable for the rotation condition, and the heat exchange enhancement under the rotation condition can keep good heat exchange uniformity of the front wall surface and the rear.
It will be appreciated by those skilled in the art that the invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The embodiments disclosed above are therefore to be considered in all respects as illustrative and not restrictive. All changes which come within the scope of or equivalence to the invention are intended to be embraced therein.
Claims (9)
1. An internally-cooled ribbed channel for an aft portion of a turbine bucket, comprising:
a channel (1) of rectangular section, hollow inside, for the passage of a fluid;
the front wall surface and the rear wall surface of the rectangular cross-section channel (1) are symmetrically provided with a plurality of inclined turbulence ribs (2); the inclined turbulence ribs (2) are arranged in an inclined mode relative to the flowing direction of the fluid;
the center of the front wall surface of the rectangular cross-section channel (1) is provided with a crossed rib (3) communicated with the inclined turbulence rib (2) on the front wall surface; the rear wall surface of the rectangular section channel (1) is not provided with a crossed rib (3) communicated with the inclined turbulence rib (2) on the rear wall surface.
2. An internally cooled ribbed channel for the aft of a turbine bucket according to claim 1 where the cross rib (3) divides the front wall face of the rectangular cross section channel (1) into two parts equally.
3. The internally cooled ribbed channel for the aft part of a turbine bucket according to claim 1, characterized in that the rib direction of the oblique turbulator ribs (2) is at an obtuse angle to the direction of the main flow subjected to the coriolis force.
4. The internally-cooled ribbed channel for the aft portion of a turbine bucket according to claim 3 wherein the rib direction is in the direction of the fins at an acute angle to the main flow direction.
5. The internally-cooled ribbed channel for the aft portion of a turbine bucket of claim 3 wherein the Coriolis force equation is Fcor ═ 2m Ω x U, where Fcor is the Coriolis force experienced by the fluid, Ω is the angular velocity of rotation of the channel, and U is the velocity of fluid movement.
6. The internally-cooled ribbed channel for the aft portion of a turbine bucket according to claim 3 wherein the rectangular cross-section channel (1) has an aspect ratio W/H of 2-4.
7. An internally cooled ribbed channel for the aft of turbine buckets according to claim 3, characterized in that the oblique turbulator ribs (2) have an angle β of 30 ° to 75 °; beta is the included angle between the inclined turbulence rib and the main flow direction of the channel.
8. The internally cooled ribbed channel for the aft of turbine buckets according to claim 3, characterized in that the cross-section of the oblique turbulator ribs (2) is square and the rib height e is1＝0.06～0.12Dh，DhThe hydraulic diameter of the channel (1) with the rectangular section is provided, and the rib spacing P is 8-12 e1。
9. The internally-cooled ribbed channel for the aft part of a turbine bucket according to claim 8, characterized in that the cross-ribs (3) are rectangular or square in cross-section, having a length in the width direction that coincides with that of the oblique turbulator ribs (2),is e1Length e in the height direction2＝0.5～1e1。
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| CN202010408311.7A CN111648830B (en) | 2020-05-14 | 2020-05-14 | Internal cooling ribbed channel for rear part of turbine moving blade |
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