专利汇可以提供Turbine blade with reverse cooling air film hole direction专利检索,专利查询,专利分析的服务。并且A gas turbine engine includes turbine blades having film cooling holes at an outer face of an airfoil wherein the film cooling holes are designed to be better filled with air. In a disclosed embodiment, the film cooling holes include a meter section extending along a direction having a main component extending from a blade tip to a blade root. In addition, a diffused section communicates with the meter section at a face of the airfoil. The diffused section is spaced toward the blade tip from the meter section. In this manner, centrifugal force ensures the diffused section is also filled with air.,下面是Turbine blade with reverse cooling air film hole direction专利的具体信息内容。
What is claimed is:
This application relates to a turbine blade, wherein the meter sections of film cooling holes extend at an angle and in a direction toward a blade root from the blade tip. In addition, a diffused section of a film cooling hole extends toward the blade tip from a meter section to receive air driven by centrifugal force.
Gas turbine engines are known, and include a plurality of sections which are typically mounted in series. Typically a fan delivers air to a compressor. Air is compressed in the compressor and delivered downstream to be mixed with fuel and combusted in a combustor section. Products of combustion move downstream over turbine rotors. The turbine rotors include a plurality of removable blades which rotate with the rotors, and are driven by the products of combustion. The turbine rotors drive components within the gas turbine engine, including the fan and compressor.
The turbine blades become quite hot from the products of combustion. Thus, it is known to pass cooling air through internal cooling passages within the turbine blades. In one known cooling technique, air is passed outwardly through holes on an outer face of an airfoil of the turbine blade, such that the cool air passes along the outer face. These film cooling holes are designed to maximize the coverage surface area on the blade, which receives the air and also to maximize the time cooling air is kept on a face of the blade.
In the prior art, the film cooling holes have a meter section that typically extend at an angle to the outer face. The angle includes a major component in a direction extending from a blade root and toward a blade tip. In addition, a diffused section extends back from this meter section towards the blade root. This type of film cooling holes is known as shaped or flared holes. The purpose of the diffused section is to slow the speed of the cooling air down as it reaches the face of the blade, such that the air would be less likely to move away from the face, and more likely to move along the face.
However, in the prior art, a centrifugal force applied as the blade rotates, moves the cooling air radially outwardly and toward the blade tip. Thus, the diffused section tends not to be filled with air. This centrifugal force and flow momentum drives the air into the radially outer portions of the holes spaced toward the tip, and leaves the diffused section less filled. Thus, the air exits the film cooling hole at a greater velocity, and does not stay on the face of the blade as long as would be desired.
In a disclosed embodiment of this invention, the meter section of film cooling holes in a turbine blade extend with a major component in a direction from the blade tip toward the blade root. A diffused section is formed to enlarge a film cooling hole at the outer face of the blade. The diffused section extends toward the blade tip from the meter section.
As the blade rotates, and cooling air exits the film cooling hole, centrifugal force forces some of the cooling air into the diffused section and the diffused section is relatively full compared to the prior art. Thus, the air exits the film cooling hole at a lower velocity than in the prior art, tends to stay on the face of the turbine blade longer, and cover a greater surface area.
These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
A gas turbine engine 10 circumferentially disposed about an engine centerline, or axial centerline axis 12 is shown in
As shown in
As shown in
As shown in
When centrifugal force acts on the air in the meter section 52, the air is driven into the diffused section 54. Flow momentum will ensure that the meter section 52 is still full. Thus, the present invention ensures the cooling air is delivered to the outer face 51 across the entirety of the film cooling holes. As can be appreciated from
In fact, the meter section can extend in the reverse direction or any direction with the diffused section extending toward the tip. Flow momentum will still fill the meter section while centrifugal force will fill the diffused section.
Although a preferred embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
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