JP5545401B2 - Turbine blade - Google Patents

Description

  The present invention relates to a turbine blade that can be cooled by a cooling gas supplied to a hollow region.

Since turbine blades provided in a turbine mounted on a jet engine or the like are exposed to high-temperature gas such as combustion gas generated by a combustor, various countermeasures against heat are taken.
As one of such measures, there is a method of suppressing overheating of the turbine blades by forming the turbine blades in a hollow state and supplying a cooling gas to the hollow region. One of the cooling methods is the impingement cooling method. The impingement cooling system is known as a cooling system that can obtain high cooling performance. However, since it is necessary to insert a component called an insert into the blade, the blade shape is limited when the impingement cooling system is used. In the current aerodynamic design, in order to improve the blade element performance, it is common to have a complicated three-dimensional shape, and the fact that the blade shape is limited so that the insert can be inserted from the viewpoint of aerodynamic design. Disadvantages.

The technique disclosed in Patent Document 1 has been proposed as a technique that exhibits the same cooling performance as impingement cooling while compensating for such drawbacks of impingement cooling.
Specifically, in the process of introducing the cooling gas from the front edge side to the rear edge side of the turbine blade, the configuration in which the cooling gas is repeatedly meandered between the back side wall surface and the abdominal side wall surface to improve the cooling efficiency is patented. It is disclosed in Document 1.

International Publication No. 07/094212 Pamphlet

By the way, in patent document 1, the meandering flow path is formed by installing alternately the slot part extended from the hub side of a turbine blade to the chip | tip side in an abdominal side wall surface and a back side wall surface.
Such a slot portion is cantilevered on either the abdominal side wall surface or the back side wall surface and extends long in the height direction of the turbine blade (the direction connecting the hub side and the tip side). Is formed.

A turbine blade having such a hollow region is manufactured by casting using a core formed of ceramics or the like. For this reason, when a plurality of slot portions are formed inside the hollow region as described above, it is necessary to form a plurality of projecting portions extending in the turbine height direction similar to the slot portions with respect to the core. is there.
However, the core is formed of ceramics or the like, and the protruding portion is long in the height direction of the turbine in a cantilevered state on a surface corresponding to the back side wall surface of the turbine blade or a surface corresponding to the abdominal side wall surface of the turbine blade. Since it is extended, stress is particularly easily applied to the bent portion.
Therefore, there is a possibility that the shape is restricted from the viewpoint of core strength. Moreover, even if it can be manufactured, the yield of the core may be deteriorated.

  The present invention has been made in view of the above-described problems, and proposes a structure that increases the rigidity of the core, increases the degree of freedom in designing the internal structure, and by using an optimal structure, and consequently, the turbine blade. The purpose is to further improve the cooling efficiency.

  The present invention adopts the following configuration as means for solving the above-described problems.

  A first aspect of the present invention is a turbine blade that can be cooled by a cooling gas supplied to a hollow region, and a meandering flow path for guiding the cooling gas to meander between a back side wall surface and an abdominal side wall surface repeatedly from the hub side. A configuration is adopted in which the cooling gas is meandered in a repeating pattern in which a plurality of adjacent meandering channels are arranged continuously toward the side and the adjacent meandering channels are different.

  According to a second aspect of the present invention, in the first aspect of the present invention, a configuration is adopted in which the repeating patterns of the adjacent meandering channels have the same period and the phase is shifted by a half period.

  According to a third aspect, in the first aspect, a configuration is adopted in which the repeating pattern of the adjacent meandering channels has the same period and the phase is shifted by a quarter period.

  4th invention is a part of the wall part which comprises the said meandering flow path in any one of the said 1st-3rd invention, The width | variety of the protrusion part which protrudes from the said back side wall surface and the said abdominal side wall surface, A configuration in which the width of the flow path from the back side wall surface to the abdominal side wall surface of the meandering flow path and the width of the flow path from the abdominal side wall surface to the back side wall surface of the meandering flow path are set wider Is adopted.

According to the present invention, a plurality of meandering channels are continuously arranged in the turbine blade height direction (the direction connecting the hub side and the tip side), and the adjacent meandering channels meander the cooling gas in different repeating patterns. Let
In other words, according to the present invention, the arrangement patterns of the protruding portions (slot portions) protruding from the back side wall surface or the abdominal side wall surface in the adjacent meandering flow paths are different. For this reason, the protrusions are discretely arranged in the height direction of the turbine blade, and are cantilevered on the back side wall surface or the abdominal side wall surface and extend long in the height direction like conventional turbine blades. There is no need to provide a slot portion to be used.
Therefore, in the core used for manufacturing such a turbine blade, it is not necessary to form a protrusion that extends long in a straight line in the height direction on the surface corresponding to the abdominal wall surface. That is, it is not necessary to form a particularly fragile portion in the conventional core. Therefore, for example, in the case where the core is allowed to have the same degree of brittleness as in the prior art, it is possible to make the core finer, for example, by narrowing the interval between the protrusions in the core.
As described above, according to the present invention, a structure that increases the rigidity of the core is proposed, the degree of freedom in designing the internal structure is increased, and the optimum structure is used, thereby further improving the cooling efficiency of the turbine blades. It becomes possible.

It is a perspective view which shows the structure of the turbine blade in 1st Embodiment of this invention. It is the arrow line view which abbreviate | omitted the abdomen while seeing the turbine blade in 1st Embodiment of this invention from the abdominal side. It is the sectional view on the AA line in FIG. It is the BB sectional view taken on the line in FIG. It is the schematic diagram which looked at the belly side protrusion part and back side protrusion part with which the turbine blade in 1st Embodiment of this invention is provided from the height direction of the turbine blade. It is the arrow line view which abbreviate | omitted the abdominal part while seeing the turbine blade in 2nd Embodiment of this invention from the abdominal side. It is the schematic diagram which looked at the belly side protrusion part with which the turbine blade in 2nd Embodiment of this invention is equipped, and the back side protrusion part from the height direction of the turbine blade. It is the arrow line view which abbreviate | omitted the abdomen while seeing the turbine blade in 3rd Embodiment of this invention from the abdominal side. It is the schematic diagram which looked at the belly side protrusion part with which the turbine blade in 3rd Embodiment of this invention is equipped, and the back side protrusion part from the height direction of the turbine blade. It is the arrow line view which abbreviate | omitted the abdomen while seeing the turbine blade in 4th Embodiment of this invention from the abdominal side.

  Hereinafter, an embodiment of a turbine blade according to the present invention will be described with reference to the drawings. In the following drawings, the scale of each member is appropriately changed in order to make each member a recognizable size.

(First embodiment)
FIG. 1 is a perspective view showing a configuration of a turbine blade 10 of the present embodiment.
The turbine blade 10 shown in FIG. 1 is a turbine blade formed of metal, but the turbine blade of the present invention is not limited to a turbine blade, and can be applied to a turbine stationary blade. .
The turbine blade 10 is exposed to a fluid flowing from the front edge portion 1 toward the rear edge portion 2, and is abdomen 3 that is curved so as to be recessed in front of the paper surface, and a back portion 4 that is curved so as to swell on the back side of the paper surface. have.
In FIG. 1, the direction connecting the hub side that is the inner diameter side with respect to the rotating shaft of the turbine and the tip side that is the outer diameter side with respect to the rotating shaft is the height direction of the turbine blade.

The turbine blade 10 includes a hollow region 5 inside and a plurality of meandering channels 6 formed in the hollow region 5.
The hollow region 5 is an internal space of the turbine blade 10 formed from a substantially central portion in the direction from the front edge portion 1 to the rear edge portion 2 to the vicinity of the rear edge portion 2. A supply flow path 7 for supplying a cooling gas to the hollow region 5 is connected to the front edge 1 side of the hollow region 5. Further, the rear edge 2 side of the hollow region 5 is an opening end 51 formed toward the rear edge 2.

  The meandering channel 6 causes the cooling gas supplied to the hollow region 5 through the supply channel 7 to meander repeatedly between the back side wall surface 5b and the abdominal side wall surface 5a (see FIG. 3), thereby leading the front edge 1 side. It leads toward the rear edge portion 2 side (rear edge side) from the (front edge side).

In the turbine blade 10 of the present embodiment, a plurality of meandering channels 6 are continuously arranged in the height direction of the turbine blade 10, and the adjacent meandering channels are cooled by different repeating patterns (meandering patterns). Let the gas meander.
Specifically, in the turbine blade 10 of the present embodiment, the repeating patterns of the adjacent meandering channels 6 are shifted in the same cycle and the phase is shifted by a half cycle.

  This will be described in more detail. FIG. 2 is an arrow view in which the abdomen 3 is omitted while the turbine blade 10 is viewed from the abdomen side. FIG. 3 is a cross-sectional view taken along line AA in FIG. 2, and is a cross-sectional view of the meandering channel 6 a on the hub side of two adjacent meandering channels 6. 4 is a cross-sectional view taken along line B-B in FIG. 2, and is a cross-sectional view of the meandering flow path 6 b on the chip side among two adjacent meandering flow paths 6.

As shown in FIGS. 3 and 4, the meandering flow path 6 includes a ventral protrusion 6 c that protrudes from the abdominal wall surface 5 a in the hollow region 5 and has a distal end surface that is separated from the back side wall surface 5 b, and a back in the hollow region 5. The rear side protruding portions 6d that protrude from the side wall surface 5b and whose front end surface is separated from the abdominal side wall surface 5a are alternately arranged.
In order to facilitate visual recognition, FIG. 2 (the same applies to FIG. 5 later) shows a plurality of points on the ventral protrusion 6c and the back protrusion 6d that constitute the meandering flow path 6a. The ventral protrusion 6c and the back protrusion 6d constituting the meandering flow path 6b are shown without a dot. Moreover, the back side protrusion part 6d which comprises the meandering flow path 6b is filled and shown.

FIG. 2 is an arrow view in which the abdomen 3 is omitted while the turbine blade 10 is viewed from the abdomen as described above, and the surface of the abdomen protrusion 6c connected to the abdomen 3 is shown with hatching. Yes.
As shown in FIGS. 2 to 4, the arrangement interval between the ventral protrusion 6 c and the back protrusion 6 d is set equal in the meandering flow path 6 a and the meandering flow path 6 b (that is, adjacent meandering flow). The repetitive pattern of the path 6 has the same period), and further, the ventral protrusions 6c and the back protrusions 6d are alternately arranged in the height direction of the turbine blades 10 (that is, adjacent meandering channels 6). The phase of the repetitive pattern is shifted by half a cycle).

  FIG. 5 is a schematic view of the ventral protrusion 6 c and the back protrusion 6 d as viewed from the height direction of the turbine blade 10. And as shown in this figure, the abdominal side protrusion part 6c and the back | dorsal side protrusion part 6d are piled up seeing from the height direction of the turbine blade 10, and are arrange | positioned.

  In the turbine blade 10 of the present embodiment having such a configuration, the cooling gas supplied to the hollow region 5 via the supply flow path 7 flows from the front edge side to the rear edge side, and the back wall surface in the meandering flow path 6. After being meandered repeatedly between 5b and the abdominal wall surface 5a, it is discharged outside.

Here, in the turbine blade 10 of the present embodiment, the repeating pattern of the meandering channel 6a and the repeating pattern of the meandering channel 6b adjacent to the meandering channel 6a are shifted in phase by a half cycle. .
Therefore, as shown in FIG. 5, when the cooling gas Y1 flows from the back side wall surface 5b toward the abdominal wall surface 5a in the meandering channel 6a, the abdominal side wall surface 5a and the back side wall surface 5b in the serpentine channel 6b. The cooling gas Y2 flows toward. On the other hand, when the cooling gas Y1 flows from the abdominal wall surface 5a toward the back side wall surface 5b in the meandering channel 6a, the cooling gas flows from the back side wall surface 5b toward the abdominal wall surface 5a in the serpentine channel 6b.

According to the turbine blade 10 of this embodiment, a plurality of meandering flow paths 6 are continuously arranged in the height direction of the turbine blade 10, and the adjacent meandering flow paths 6 meander the cooling gas in different repeating patterns. Let
That is, according to the turbine blade 10 of the present embodiment, the arrangement patterns of the ventral protrusions 6c and the back protrusions 6d are different in the adjacent meandering flow paths 6. For this reason, the abdominal projection 6c and the dorsal projection 6d are discretely arranged in the height direction of the turbine blade 10, and the back side wall surface or the abdominal side wall surface is separated as in the conventional turbine blade. It is not necessary to provide a slot portion that is held and extends long in the height direction.
Therefore, in the core used for manufacturing such a turbine blade, it is not necessary to form a protrusion that extends long in a straight line in the height direction on the surface corresponding to the abdominal wall surface. That is, it is not necessary to form a particularly fragile portion in the conventional core. Therefore, for example, in the case where the core is allowed to have the same degree of brittleness as in the prior art, it is possible to make the core finer, for example, by narrowing the interval between the protrusions in the core.
As described above, according to the turbine blade 10 of the present embodiment, a structure that increases the rigidity of the core is proposed, the degree of freedom in designing the internal structure is increased, and the optimum structure is used, thereby cooling the turbine blade. Efficiency can be further improved.

(Second Embodiment)
Next, a second embodiment of the present invention will be described. In the description of the present embodiment, the description of the same parts as those of the first embodiment is omitted or simplified.

  FIG. 6 is an arrow view in which the abdomen 3 is omitted while the turbine blade 10 of this embodiment is viewed from the abdomen side. FIG. 7 is a schematic view of the ventral protrusion 6 c and the back protrusion 6 d provided in the turbine blade 10 as viewed from the height direction of the turbine blade 10.

As shown in these drawings, in the turbine blade 10 of the present embodiment, the repeating patterns of the adjacent meandering flow paths 6a and 6b have the same period and the phase is shifted by a quarter period.
By adopting such a configuration, as shown in FIG. 7, when viewed from the height direction of the turbine blade 10, a meandering flow is formed between the ventral protrusion 6c and the back protrusion 6d of the meandering passage 6a. The ventral protrusion 6c and the dorsal protrusion 6d of the path 6b are arranged.

  For this reason, it can suppress that a cooling gas moves between the adjacent meandering flow paths 6a and 6b. For example, when the turbine blade 10 is a moving blade, centrifugal force or the like acts on the turbine blade 10, and the cooling gas may be biased in the hollow region 5. On the other hand, according to the turbine blade 10 of the present embodiment, it is possible to suppress the movement of the cooling gas between the adjacent meandering flow paths 6a and 6b, and thus it is possible to suppress the deviation of the cooling gas. The entire turbine blade 10 can be reliably cooled.

(Third embodiment)
Next, a third embodiment of the present invention will be described. In the description of the present embodiment, the description of the same parts as those in the first and second embodiments is omitted or simplified.

  FIG. 8 is an arrow view in which the abdomen 3 is omitted while the turbine blade 10 of this embodiment is viewed from the abdomen side. FIG. 9 is a schematic view of the ventral protrusion 6 c and the back protrusion 6 d provided in the turbine blade 10 as viewed from the height direction of the turbine blade 10.

As shown in these drawings, in the turbine blade 10 of the present embodiment, the repeating pattern of the adjacent meandering channels 6a and 6b has the same period and the phase is shifted by a quarter period, and further, the ventral protrusion 6c. And the width of the back projecting portion 6d is the width d of the flow path from the back side wall surface 5b of the meandering flow path 6 to the abdominal side wall face 5a and the flow path from the abdominal side wall face 5a of the meandering flow path 6 to the back side wall face 5b. By adopting such a configuration, which is set wider than the width d of the turbine blade 10, as shown in FIG. Between the side protrusions 6d, the ventral side protrusions 6c and the back side protrusions 6d of the meandering flow path 6b are disposed so as to overlap each other.

For this reason, it is possible to further suppress the movement of the cooling gas between the adjacent meandering channels 6a and 6b than the turbine blade 10 of the second embodiment.
Therefore, according to the turbine blade 10 of the present embodiment, it is possible to suppress the movement of the cooling gas between the adjacent meandering flow paths 6a and 6b. The entire turbine blade 10 can be cooled.

(Fourth embodiment)
Next, a fourth embodiment of the present invention will be described. In the description of the fourth embodiment, the description of the same parts as those of the first to third embodiments will be omitted or simplified.

FIG. 10 is a view of the turbine blade 10 of the present embodiment as viewed from the abdomen side and omitting the abdomen 3.
As shown in this figure, the turbine blade 10 of this embodiment includes the meandering flow path 6 (meandering flow path 61) of the first embodiment in the area A on the tip side of the hollow area 5, and the center of the hollow area 5 The region B is provided with the meandering channel 6 (meandering channel 62) of the second embodiment, and the region C on the hub side of the hollow region 5 is provided with the meandering channel 6 (meandering channel 63) of the third embodiment. ing.

  According to the turbine blade 10 of the present embodiment having such a configuration, the cooling efficiency varies depending on the region in the height direction, and cooling according to the heating state of the turbine blade 10 can be realized.

  As mentioned above, although preferred embodiment of this invention was described referring an accompanying drawing, it cannot be overemphasized that this invention is not limited to the said embodiment. Various shapes, combinations, and the like of the constituent members shown in the above-described embodiments are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.

  For example, the repeating pattern of the meandering channel 6 shown in the above embodiment, that is, the arrangement pattern of the back side wall surface 5b and the abdominal side wall surface 5a is an example, and can be arbitrarily changed according to the cooling performance required for the turbine blade. .

  Moreover, although the example shown in the said embodiment showed the example which applied this invention to the cooling channel | path of the blade trailing edge part, you may apply to the other site | part of a blade.

  DESCRIPTION OF SYMBOLS 10 ... Turbine blade, 1 ... Front edge part, 2 ... Rear edge part, 3 ... Abdominal part, 4 ... Back part, 5 ... Hollow area, 5a ... Abdominal side wall surface, 5b ... Back side wall surface, 6 (6a, 6b) ... meandering flow path, 6c ... ventral protrusion (protrusion, wall), 6d ... dorsal protrusion (protrusion, wall), Y1, Y2 ... cooling gas

Claims (1)

A turbine blade capable of being cooled by a cooling gas supplied to a hollow region,
A plurality of meandering flow paths that continuously guide the cooling gas between the back side wall surface and the abdominal side wall face are arranged from the hub side toward the chip side, and the adjacent meandering flow paths have different repeating patterns. Meander the cooling gas,
The repeating pattern of adjacent meandering channels has the same period and the phase is shifted by a quarter period,
The width of the protruding portion protruding from the back side wall surface and the abdominal side wall surface, which is a part of the wall portion constituting the meandering flow path, is a flow path from the back side wall surface of the serpentine flow path toward the abdominal side wall surface. And a width of a flow path extending from the abdominal side wall surface of the meandering flow path to the back side wall surface.

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