JP5239903B2 - Turbine blade - Google Patents

Description

  The present invention relates to a turbine blade in which an insert for impingement cooling the blade body is installed inside a hollow blade body.

In a turbine blade exposed to a high temperature environment, the turbine blade is cooled in order to suppress a decrease in life due to thermal damage.
For example, Patent Documents 1 to 4 describe a turbine blade in which an insert in which a plurality of impingement holes are formed is installed inside the turbine blade in order to efficiently cool the turbine blade.
This insert includes a plurality of impingement holes formed toward the blade body of the turbine blade, and the inside is hollow. Then, the cooling gas supplied to the inside of the insert is blown onto the inner wall surface of the blade body through the impingement hole, so that the blade body is so-called impingement cooled.

By the way, between the insert and the blade body, the cooling gas ejected from the impingement hole flows along the surface of the insert and the inner surface of the blade body.
When such a flow of cooling gas after jetting (hereinafter referred to as “cooling gas flow after jetting”) is formed between the insert and the blade body, the impingement hole located on the downstream side of the cooling gas flow after jetting It becomes difficult for the injected cooling gas to flow into the cooling gas flow after jetting and reach the blade body. Therefore, the effect of impingement cooling becomes weaker toward the downstream side of the cooling gas flow after ejection.

On the other hand, Patent Document 1 proposes a configuration in which an insert support for fixing the insert to the blade body is arranged on the upstream side of the impingement hole.
According to such a configuration of Patent Document 1, it is possible to suppress the intrusion of the cooling gas flow formed between the insert and the blade main body into the region between the impingement hole and the blade main body, and efficiently. Impingement cooling can be performed.

JP-A-7-19002 JP-A-6-330705 JP 58-187502 A JP-A-3-79522

However, since it is necessary to cool the entire blade body, a large number of impingement holes are formed in the entire insert. On the other hand, the insert support supports the insert, and the number of the insert supports is obviously small with respect to the impingement hole, and the shape is limited to a shape suitable for supporting the insert.
Therefore, in the configuration in which the conventional insert support is arranged on the upstream side of the impingement hole, the number of impingement holes that can ensure that the cooling gas reaches the blade body is limited, so that the impingement cooling efficiency can be improved sufficiently. difficult.

  The present invention has been made in view of the above-described problems, and an object of the present invention is to further improve the impingement cooling efficiency of the blade body in the turbine blade.

  The present invention adopts the following configuration in order to solve the above problems.

  According to a first aspect of the present invention, a hollow wing body is fixed to the wing body via an insert support, thereby being installed inside the wing body and injecting a cooling gas toward the inner wall surface of the wing body. A turbine blade including an insert having an impingement hole, wherein the cooling gas flow after injection is shielded from the cooling gas flow that is formed by the cooling gas after being ejected from the impingement hole, and the cooling gas flow after the ejection A configuration is adopted in which shielding means installed at least upstream of the impingement hole is provided separately from the insert support.

  A second invention adopts a configuration in the first invention, wherein the shielding means is a shielding wall standing at least upstream of the impingement hole with respect to the cooling gas flow after ejection.

  According to a third invention, in the second invention, the shield wall has a configuration in which a plan view shape with respect to the installation surface has a shape in which a central portion protrudes toward the upstream side of the cooling gas flow after the ejection. .

  According to a fourth aspect of the present invention, in the second aspect of the present invention, the shield wall is erected so as to surround the impingement hole.

According to the present invention, the shielding means provided separately from the insert support suppresses the cooling gas flow from entering the region between the impingement hole and the blade body after ejection.
Therefore, it is possible to install a necessary number of shielding means at necessary locations without being affected by the arrangement of the insert support.
Therefore, according to the present invention, the impingement cooling efficiency of the blade body can be further improved.

It is sectional drawing which shows schematic structure of the turbine blade in 1st Embodiment of this invention. It is a perspective view of an insert with which a turbine blade in a 1st embodiment of the present invention is provided. It is a plane enlarged view containing the shielding wall with which the turbine blade in 1st Embodiment of this invention is provided. It is a plane enlarged view which shows the modification of the shielding wall with which the turbine blade in 1st Embodiment of this invention is provided. It is sectional drawing which shows the modification of the shielding wall with which the turbine blade in 1st Embodiment of this invention is provided. It is side surface sectional drawing containing the shielding wall with which the turbine blade in 2nd Embodiment of this invention is provided. It is a perspective view containing the shielding wall with which the turbine blade in 3rd Embodiment of this invention is provided. It is sectional drawing containing the shielding wall with which the turbine blade in 3rd Embodiment of this invention is provided.

  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 cross-sectional view showing a schematic configuration of a turbine blade 1 of the present embodiment.
As shown in this figure, the turbine blade 1 of the present embodiment is provided with a blade body 2 and an insert 3.

The blade body 2 forms the outer shape of the turbine blade 1 of the present embodiment, and has an internal space 2a by making the inside hollow.
The wing body 2 includes a front edge portion 2b and a rear edge portion 2c. A through hole 2d that communicates from the internal space 2a to the outside of the wing body 2 is formed in the rear edge portion 2c.

The insert 3 is supported by the insert support 4 that connects the wing body 2 and the insert 3, so that the insert 3 is accommodated in the inner space 2 a of the wing body 2 while being spaced apart from the inner wall surface of the wing body 2 by a certain distance. Yes.
The insert support 4 is fixed to the surface of the insert 3. Then, the insert 3 is supported by the front end side of the insert support 4 being brought into contact with the inner wall surface of the wing body 2.

FIG. 2 is a perspective view of the insert 3. As shown in this figure, the insert 3 has a similar external shape that is substantially the same as the external shape of the internal space 2a of the wing body 2, and the internal space 3a is provided by making the inside hollow. Yes.
As shown in FIG. 2, the insert 3 has a plurality of impingement holes 3 b formed toward the inner wall surface of the wing body 2.
Note that cooling gas is supplied to the internal space 3a of the insert 3, and the cooling gas is blown onto the inner wall surface of the blade body 2 via the impingement hole 3b, whereby the blade body 2 is impinged.

Further, the cooling gas ejected from the impingement hole 3b flows between the insert 3 and the inner wall surface of the blade body 2 toward the rear edge 2c. That is, between the insert 3 and the inner wall surface of the blade body 2, a post-injection cooling gas flow R that is formed by the cooling gas after the injection and flows toward the rear edge 2 c is formed.
And the turbine blade 1 of this embodiment is provided with the shielding wall 5 (shielding means) which suppresses that the cooling gas flow R penetrate | invades into the area | region between the impingement hole 3b and the inner wall face of the blade body 2 after injection. Yes.

The shielding wall 5 is provided separately from the insert support 4 and is erected on the upstream side (upstream side in the direction of fluid flow R) of each impingement hole 3b as shown in the enlarged plan view of FIG. . The shielding wall 5 is fixed to the insert 3.
Then, as shown in the enlarged plan view of FIG. 3, the shielding wall 5 has two walls 5a such that the planar shape with respect to the installation surface is a shape in which the central portion projects toward the upstream side in the fluid flow R direction. And the wall 5b are connected with an angle.

  In the turbine blade 1 of the present embodiment having such a configuration, the cooling gas supplied to the inner space 3a of the insert 3 is ejected through the impingement hole 3b and blown onto the inner wall surface of the blade body 2 to cause the blade. The main body 2 is impingement cooled. As shown in FIG. 3, the shielding wall 5 prevents the post-injection cooling gas flow R from entering the region between the impingement hole 3 b and the inner wall surface of the blade body 2. For this reason, it is suppressed that the cooling gas ejected from the impingement hole 3b flows into the cooling gas flow R after the ejection, and the cooling gas ejected from the impingement hole 3b is more reliably sprayed to the inner wall surface of the blade body 2. Is possible.

According to the turbine blade 1 of the present embodiment as described above, the post-injection cooling gas flow formed between the insert 3 and the blade body 2 by the shielding wall 5 provided separately from the insert support 4. R is prevented from entering the region between the impingement hole 3 b and the blade body 2.
Therefore, it is possible to install a necessary number of shielding walls 5 at a necessary location without being affected by the arrangement of the insert support 4 and the like, and shield each impingement hole 3b as in the turbine blade 1 of the present embodiment. The wall 5 can be installed.
Therefore, according to the turbine blade 1 of the present embodiment, the impingement cooling efficiency of the blade body 2 can be further improved.

  Further, according to the turbine blade 1 of the present embodiment, since the impingement cooling efficiency is improved, the amount of cooling gas used can be reduced when the turbine blade 1 is cooled to a desired temperature.

Moreover, in the turbine blade 1 of the present embodiment, the shape of the shielding wall 5 is a shape in which the central portion protrudes toward the upstream side of the cooling gas flow R after the ejection.
For this reason, generation | occurrence | production of the turbulent flow when the cooling gas flow R after jetting passes the shielding wall 5 can be suppressed, and the pressure loss between the insert 3 and the inner wall surface of the blade body 2 can be reduced.

In the turbine blade 1 of the present embodiment, the two walls 5a and 5b are connected with an angle so that the shape of the shielding wall 5 is centered toward the upstream side of the cooling gas flow R after the jet. The part protrudes.
However, the present invention is not limited to this, and as shown in FIGS. 4 and 5, the shielding wall 5 is curved so that the central portion protrudes toward the upstream side of the cooling gas flow R after jetting. It may be formed.
The tip of the shielding wall 5 may be in contact with the inner wall surface of the wing body 2.

(Second Embodiment)
Next, a second embodiment of the present invention will be described. In the description of the second embodiment, the description of the same parts as in the first embodiment will be omitted or simplified.
FIG. 6 is a side sectional view including the shielding wall 6 provided in the turbine blade of the present embodiment.
As shown in this figure, the shielding wall 6 provided in the turbine blade of the present embodiment is installed inclined from the upstream side to the downstream side of the cooling gas flow R after jetting so as to form an acute angle with the installation surface. May be.
Further, the shielding wall 6 is erected on the insert 3 such that the tip portion is separated from the inner wall surface of the wing body 2.

  According to the turbine blade of this embodiment having such a configuration, the thickness of the post-injection cooling gas flow R formed between the impingement hole 3b and the inner wall surface of the blade body 2 can be reduced. The post-injection cooling gas flow R entering the region between 3b and the inner wall surface of the blade body 2 can be reduced.

Also in the turbine blade of the present embodiment having such a configuration, similarly to the first embodiment, the cooling gas ejected from the impingement hole 3b is suppressed from flowing into the cooling gas flow R after the ejection, and the impingement hole It becomes possible to reliably blow the cooling gas ejected from 3b onto the inner wall surface of the blade body 2.
And it becomes possible not to be influenced by arrangement | positioning of the insert support 4, etc., and it becomes possible to install the required number of shielding walls 5 in a required location, and the shielding wall 6 can be installed with respect to each impingement hole 3b.
Therefore, according to the turbine blade of the present embodiment, the impingement cooling efficiency of the blade body 2 can be further improved.

(Third embodiment)
Next, a third embodiment of the present invention will be described. In the description of the third embodiment, the description of the same parts as those of the first embodiment will be omitted or simplified.
FIG. 7 is a perspective view including the shielding wall 7 provided in the turbine blade of the present embodiment. FIG. 8 is a cross-sectional view including the shielding wall 7 provided in the turbine blade of the present embodiment.
As shown in these drawings, the shielding wall 7 included in the turbine blade of the present embodiment is installed so as to surround the impingement hole 3b.
Further, the shielding wall 7 is erected on the insert 3 such that the tip portion is separated from the inner wall surface of the wing body 2.

According to the turbine blade of this embodiment having such a configuration, the thickness of the post-injection cooling gas flow R formed between the impingement hole 3b and the inner wall surface of the blade body 2 can be reduced. The cooling gas flow R after jetting into the region between 3b and the inner wall surface of the blade body 2 can be reduced.
Further, since the shielding wall 7 surrounds the impingement hole 3b, it is possible to prevent the cooling gas flow R from flowing around after being ejected from the downstream side of the impingement hole 3b toward the impingement hole 3b.
Therefore, according to the turbine blade of the present embodiment, the impingement cooling efficiency of the blade body 2 can be further improved.

  As mentioned above, although preferred embodiment of this invention was described referring drawings, 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, in the above-described embodiment, the configuration in which the inside of the wing body 2 is a single space and the single insert 3 is installed therein has been described.
However, the present invention is not limited to this. For example, the inside of the wing body 2 may be divided into a plurality of spaces by a partition plate or the like, and an insert may be installed in each space.

Moreover, in the said embodiment, the structure by which one shielding wall was installed with respect to each impingement hole 3b was demonstrated.
However, the present invention is not limited to this, and it is not always necessary to provide a shielding wall for all impingement holes 3b.
A plurality of shielding walls may be installed for one impingement hole 3b.

Moreover, in the said embodiment, the structure where the shape of the impingement hole 3b was circular was demonstrated.
However, the present invention is not limited to this, and the impingement hole 3b may have another shape such as an ellipse or an oval.

Moreover, in the said embodiment, the structure which uses a shielding wall as a shielding means of this invention was demonstrated.
However, the present invention is not limited to this, and for example, a sheet member or a film member can be used as the shielding means of the present invention.

  DESCRIPTION OF SYMBOLS 1 ... Turbine blade, 2 ... Blade body, 2a ... Internal space, 3 ... Insert, 3a ... Internal space, 3b ... Impingement hole, 4 ... Insert support, 5, 6, 7 ... Shielding wall (Shielding means), R ... Cooling gas flow after ejection

Claims (2)

A hollow wing body, and an insert having an impingement hole that is installed inside the wing body by being fixed to the wing body via an insert support and that ejects cooling gas toward the inner wall surface of the wing body; A turbine blade comprising:
Shielding means installed at least upstream of the impingement hole for shielding the post-injection cooling gas flow and shielding the post-injection cooling gas flow that is a flow formed by the cooling gas after being ejected from the impingement hole; Provided separately from the insert support ,
The shielding means is a shielding wall standing at least upstream of the impingement hole with respect to the cooling gas flow after the ejection,
The shielding wall has a shape in which a plan view shape with respect to the installation surface has a center portion protruding toward the upstream side of the flow of the cooling gas after jetting, is spaced from the impingement hole, and a tip portion is an inner wall surface of the blade body A turbine blade, wherein the turbine blade is provided so as to be separated from the turbine blade. The shielding wall turbine blade according to claim 1, wherein the surrounding the periphery of said impingement holes are erected.

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