JPH0719002A - Turbine blade having cooling flow passage - Google Patents

Abstract

PURPOSE:To improve cooling effect by inserting an insert member in the hollow hole of a turbine blade, providing a supporting column for forming a cooling flow passage in which a clearance is set between the insert member and the inner wall surface of the hollow hole, and arranging a hole which allows cooling air to be blown out from the insert member on a vicinity shifted downstream from the supporting column body. CONSTITUTION:The blade main body 10 of a turbine blade is formed in a hollow structure, a plurality of hollow holes 13A, 13B enclosed by a side wall 11 and a bulkhead 12 are formed, and a cooling hole 11a and an exhaust port 11b which allows blowing out of a part of cooling air which passes through cooling passages 15A, 15B are provided on the side wall 11. Insert members 14A, 14B are formed in hollow structures having air chambers 14a, 14b, respectively, and a blowout hole 14c is opened to the outside cooling passages 15A, 15B. The blowout hole 14c is arranged in the vicinity of a position which is shifted downstream from a supporting column 16 for supporting the insert members 14A, 14B. Parallel flow of cooling air is disturbed by the supporting column 16, new cooling air is blown out from the blowout hole 14c toward the position where cooling air is weakened in a backward vicinity so as to improve cooling effect.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine blade having a cooling passage.

[0002]

2. Description of the Related Art FIG. 4 shows an example of a turbine blade having a cooling flow path. A plurality of turbine blades are provided on an outer peripheral portion of a support disk 1 which is rotated around a rotation axis X as indicated by an arrow. 2 is fixed.

Inside the turbine blade 2, a meandering cooling passage 3 is formed to allow cooling air to pass therethrough, and to suppress the temperature rise of the turbine blade 2 due to the influence of high temperature gas below an allowable value. Is set to.

FIG. 5 shows another structural example of a turbine blade having a cooling flow path. In order to reduce the weight and secure the strength of the turbine blade, the turbine blade (blade body) 2 has a hollow structure, and the side wall 5 surrounding the hollow hole 4 is thinned, while While inserting the insert member 6 having the air chamber 6a, a plurality of support columns 7 are arranged between the insert member 6 and the side wall 5, and the cooling channel 3 is formed by the gap between the insert member 6 and the side wall 5. To secure. Further, as shown by the arrows in FIG. 6, the cooling air sent into the air chamber 6a of the insert member 6 is jetted in a shower shape from the jet holes 6b toward the side wall 5, and a new air is generated near the inner surface of the side wall 5. Cooling air is sent to accelerate the cooling of the side wall 5 of the blade body 2, and at the same time, a part of the cooling air is jetted from the cooling hole 5a to the surface of the side wall 5 to suppress the temperature rise of the surface.

[0005]

However, all of these techniques still have problems to be solved in terms of cooling effect. That is, when the cooling air is passed along the cooling flow path 3, the cooling air becomes a parallel flow and a cooling air layer (cooling air film) C is formed near the inner surface of the side wall 5. Air layer C is the ejection hole 6b
There is still a technical problem that the cooling efficiency is lowered due to the phenomenon that the cooling air flow from the inside is blocked to prevent the cooling air in the low temperature state from reaching the inner surface of the side wall 5.

The present invention has been made in view of these problems, and an object thereof is to make air in a new low temperature state reach the inner surface of the side wall of the blade body to improve the cooling effect.

[0007]

In a turbine blade having a cooling passage according to the present invention, a blade body having a hollow hole formed therein, and an air chamber inserted into the hollow hole of the blade body and supplied with cooling air. And an insert member having an ejection hole for ejecting the stored cooling air, and an insertion member disposed between the insert member and the inner wall surface of the hollow hole to set a gap to form a cooling flow path around the insert member. A support column is provided, and the ejection hole of the insert member is arranged at a position near the column shifted from the support column in the downstream direction of the cooling flow path.

[0008]

The cooling air sent into the air chamber of the insert member is temporarily stored in the air chamber and then ejected from the ejection holes into the cooling passage. At this time, if a cooling air flow is generated in the cooling channel, the blade body is cooled from the inside,
The cooling air flow is disturbed by intersecting with the support columns. When new cooling air is ejected to the disturbed portion of the cooling air flow through the ejection holes, the low temperature air reaches the inner surface of the side wall of the blade body and cools it, thereby improving the cooling effect. .

[0009]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT An embodiment of a turbine blade having a cooling passage according to the present invention will be described below with reference to FIGS. In each drawing, reference numeral 10 is a blade main body, 11 is a side wall, 12 is a partition wall, 13A and 13B are hollow holes, and 14A and 1
4B is an insert member, 15A and 15B are cooling channels, 1
6 is a support pillar.

The blade body 10 has a hollow structure, and a plurality of hollow holes 13 surrounded by a side wall 11 and a partition wall 12.
A and 13B are provided, and a cooling hole 11a for cooling the outer surface by ejecting a part of the cooling air passing through the cooling flow paths 15A and 15B is formed in an appropriate portion of the side wall 11, and the edge portion is formed. Exhaust port 11 with hollow hole 13B connected to the outside
b is formed.

The insert members 14A and 14B are respectively inserted into the plurality of hollow holes 13A and 13B of the blade body 10, and the cooling passages 15A and 1 are provided between the insert members 14A and 14B and the side wall 11 around them.
5B is formed, and is a hollow structure having air chambers 14a and 14b into which cooling air is sent.
A number of ejection holes 14c for connecting a and 14b and the outside thereof (cooling channels 15A and 15B) are appropriately opened.

A support pillar 16 for ensuring the cooling flow passages 15A, 15B is provided between the inner wall surface of the side wall 11 and the insert members 14A, 14B by interposing a gap therebetween. The cooling channels 15A and 15B are arranged in an intersecting state.

Further, as shown in FIG. 2, the ejection holes 14c of the insert members 14A, 14B are set so as to be arranged at positions near the support columns 16 and displaced in the downstream direction of the cooling channels 15A, 15B. It

In the turbine blade having the cooling passage thus configured, the insert members 14A, 14B
When the cooling air is sent into the air chambers 14a and 14b of the cooling chamber, the cooling air is temporarily stored in the air chambers 14a and 14b, and then the cooling passage 15 is ejected from the ejection holes 14c at a plurality of locations.
Into A and 15B, for example, it is jetted like a shower.

Then, as shown in FIG. 2, a part of the cooling air flows along the cooling flow paths 15A and 15B, and the side wall 1
Cooling the side wall 11 from the inner surface by contact with the inner surface of 1,
It gradually leads to a parallel flow.

Further, the cooling air passing through the cooling flow paths 15A and 15B intersects with the support columns 16 to disturb the parallel flow, so that the cooling air is weakened in the rear vicinity of the support columns 16. In this case, when the cooling air is ejected from the ejection holes 14c opened in the vicinity of the cooling columns 15A and 15B, which are displaced from the support columns 16 in the downstream direction, as shown in FIG.
As shown in FIG. 5, the parallel flow of the cooling air is disturbed, so that the cooling air joins the part where the cooling air layer C is partially disappearing, and the new air in the low temperature state is easily formed. After reaching the inner surface of the side wall 11, the cooling is performed. In this way, the new cooling air is the cooling air layer C.
By being sent to and merged with each other, the replacement of air is promoted and the cooling effect is improved.

On the other hand, the surplus air sent to the downstream side of the cooling flow path 15B is discharged to the outside of the blade body 10 through the exhaust port 11b arranged on the side wall 11.

[Other Embodiments] In the present invention, the following technique can be adopted instead of one embodiment. a) Air chambers 14a, 14b and cooling channels 15A, 15B
Arrange any number of. b) The cross-sectional shape of the support pillar 16 is arbitrary.

[0019]

The turbine blade having the cooling passage according to the present invention has the following effects. (1) An insert member having an ejection hole for ejecting the cooling air which is inserted into the hollow hole of the blade body and ejects the cooling air, and an insert which is arranged in an interposing state between the insert member and the inner wall surface of the hollow hole to set a gap. By including a support columnar body that forms a cooling flow path around the member, and the ejection holes of the insert member are arranged in a vicinity position displaced from the support columnar body in the downstream direction of the cooling flow path. It is possible to cool the blade body efficiently by making the new low temperature air sequentially reach the inner surface of the side wall of the blade body. (2) Since it has a simple structure in which the cooling air flow is sent to the rear of the support column, it can be easily implemented. (3) By disposing the supporting columnar body in the vicinity of the ejection hole of the insert member, it is possible to prevent a reduction in strength when the weight is reduced.

[Brief description of drawings]

FIG. 1 is a cross-sectional view showing an embodiment of a turbine blade having a cooling channel according to the present invention.

FIG. 2 is a vertical cross-sectional view showing the relationship between the cooling passages, the support columns, and the ejection holes of FIG.

FIG. 3 is a schematic diagram showing a mixed state of cooling air streams in FIG.

FIG. 4 is a perspective view showing a structural example of a turbine blade having a cooling channel.

FIG. 5 is a cross-sectional view showing a conventional example of a turbine blade.

FIG. 6 is a vertical cross-sectional view showing the relationship between the cooling flow path and the ejection holes of the insert member.

[Explanation of symbols]

 10 Blade Main Body 11 Side Wall 11a Cooling Hole 11b Exhaust Port 12 Partition 13A, 13B Hollow Hole 14A, 14B Insert Member 14a, 14b Air Chamber 14c Jet Hole 15A, 15B Cooling Channel 16 Support Pillar X Rotating Axis C Cooling Air Layer (Cooling) Air film)

Claims (1)

[Claims] 1. An insert member having an airfoil body having a hollow hole formed therein, an air chamber inserted into the hollow hole of the airfoil body and into which cooling air is sent, and an ejection hole for ejecting the stored cooling air, and an insert member. A support columnar body which is disposed in an intervening state between the inner wall surface of the hollow hole and forms a cooling flow path around the insert member by setting a gap, and the ejection hole of the insert member is cooled from the support columnar body. A turbine blade having a cooling flow passage, which is arranged at a position shifted in the downstream direction of the flow passage.