Patent Application
20090169394
This invention relates to a method of forming cooling holes, and a turbine airfoil with cooling holes formed by use of two distinct hole-forming techniques.
In a gas turbine engine, air is compressed in a compressor, mixed with fuel and ignited in a combustor for generating hot combustion gases which flow downstream through one or more stages of turbine nozzles and blades. The nozzles include stationary vanes followed in turn by a corresponding row of turbine rotor blades attached to the perimeter of a rotating disk. The vanes and blades have correspondingly configured airfoils which are hollow and include various cooling circuits and features which receive a portion of air bled from the compressor for providing cooling against the heat from the combustion gases.
The turbine vane and blade cooling art discloses various configurations for enhancing cooling and reducing the required amount of cooling air in order to increase the overall efficiency of the engine while obtaining a suitable useful life for the vanes and blades. For example, typical vane and blade airfoils in the high pressure turbine section of the engine include cooling holes that extend through the pressure side, or suction side, or both, for discharging a film of cooling air along the outer surface of the airfoil to effect film cooling in a conventional manner.
A typical film cooling hole is in the form of a cylindrical aperture inclined axially through one of the airfoil sides, such as the pressure side, for discharging the film air in the aft direction. The cooling holes are typically provided in a radial or spanwise row of holes at a specific pitch spacing. In this way, the cooling holes discharge a cooling film that forms an air blanket for protecting the outer surface, otherwise known as “lands” of the airfoil from hot combustion gases during operation.
In the region of the blade leading edge, it is also known to incline the cylindrical film cooling holes at an acute span angle to position the hole outlets radially above the hole inlets and discharge the cooling film radially outwardly from the respective holes. In order to improve the performance of cooling holes, it is also conventional to modify their shape to effect cooling flow diffusion. The diffusion reduces the discharge velocity and increases the static pressure of the airflow. Diffusion cooling holes are found in patented configurations for improving film cooling effectiveness with suitable blowing ratios and backflow margin. A typical diffusion film cooling hole may be conical from inlet to outlet with a suitable increasing area ratio for effecting diffusion without undesirable flow separation. Diffusion occurs in three axes, i.e. along the length of the hole and in two in-plane perpendicular orthogonal axes. See, for example, U.S. Pat. No. 6,287,075 to the present assignee.
Other types of diffusion cooling holes are also found in the prior art including various rectangular-shaped holes, and holes having one or more squared sides in order to provide varying performance characteristics. Like conical diffusion holes, the rectangular diffusion holes also effect diffusion in three dimensions as the cooling air flows therethrough and is discharged along the outer surface of the airfoil. See, for example, U.S. Pat. Nos. 6,283,199, 5,683,600 and 5,486,093.
As turbine designs have become more complex and efficient, it has become more common for these engines to rely on complex, 3-dimensional, film cooling patterns to distribute cooling air across airfoil bodies to minimize thermal stress on the component in engine operation. The holes typically are round on the inside of the part and transition to a 3-dimensional spout upon exit at the outer wall to be cooled. The transition slows down and spreads the air more effectively across the external surfaces. These transitional holes are difficult and expensive to machine into turbine airfoils and other parts requiring critical cooling airflow.
There are two primary manufacturing technologies used to machine film cooling holes-electrical discharge machining (“EDM”) and laser machining. Each technology has significant benefits and drawbacks. EDM provides the highest quality of hole in terms of recast and surface finish. However, EDM hole formation is slow, typically entailing tens of seconds to over a minute per hole drilled. Typical gas turbine airfoils have between 100 and 500 film cooling holes. While the quality is superior, the investment required to purchase multiple machines is high.
Laser provides the fastest process to drill film cooling holes in gas turbine airfoils. However, the drawback to conventional laser drilling is that the resulting hole is of overall lower quality, which impacts the overall efficiency of the engine. The laser industry and users are developing various technologies to improve laser drilled hole quality but these advances have resulted in significantly reduced hole formation speed, as well as a more difficult to maintain and expensive laser machine. The laser technologies that can match or exceed EDM quality cannot drill complete holes due to power/energy limitations.
Generally, the turbine industry has applied EDM technology to critical components such as rotating turbine blades and laser technology to less critical applications such as non-rotating turbine vanes. Both technologies are used on both types of parts, depending on the engine model.
Therefore, there is a need to provide a more efficient way of forming cooling holes in turbine airfoils and other parts requiring critical cooling airflow.
A combination EDM and laser processes is used to form the film cooling holes in turbine airfoils, leveraging the throughput and quality strengths of both technologies. A laser system that can mill the shaped section of the hole is used to reduce the time per shape. The laser is capable of machining/micro-machining the shaped section of the hole in approximately ½ to ⅕ the time required for the same volume with an EDM process. The EDM machine is then used to drill the round through hole from the base of the shaped section. The round hole penetrates through to the internal cooling air passage within the turbine blade or vane. Holes formed by this method are referred to as being “hybrid-formed.”
According to one aspect of the invention, a method of forming a cooling hole in a workpiece includes the steps of laser-forming a blind, inwardly-tapering transition opening into a first side of the workpiece; and EDM-forming a generally cylindrical through hole to a second, opposing side of the workpiece communicating with the inwardly-tapering transition opening to form a through cooling hole communicating with the first and second sides of the workpiece.
In accordance with another aspect of the invention, the workpiece comprises an airfoil, and the step of forming the transition opening comprises the step of forming a diffuser section of the cooling hole, and the step of forming the generally cylindrical through hole comprises the step of forming a metering section of the cooling hole.
In accordance with yet another aspect of the invention, the method of forming the diffuser section includes the step of forming the diffuser section with a conical configuration.
In accordance with yet another aspect of the invention, a method of forming a plurality of cooling holes in a turbine airfoil of the type having a leading edge and an axially spaced-part trailing edge is provided. The leading edge has an axially-extending aerodynamic external surface curvature, a root and a tip spaced-apart along a radially-extending span axis, a pressure sidewall and a laterally-spaced-apart suction sidewall, and a cooling circuit positioned between the pressure sidewall and the suction sidewall for channeling a fluid flow for cooling the airfoil. The method includes the steps of laser-forming a plurality of blind, inwardly-tapering diffuser sections into a first side of the workpiece, and EDM-forming a generally cylindrical through metering section to a second, opposing side of the workpiece communicating with the inwardly-tapering transition opening to form a through cooling hole communicating with the first and second sides of the workpiece.
In accordance with yet another aspect of the invention, the method includes the step of using an inner end of the transition opening as a guide for EDM formation of the cylindrical through hole.
In accordance with yet another aspect of the invention, the method includes the step of forming the transition opening after the step of forming the cylindrical through hole.
In accordance with yet another aspect of the invention, an airfoil is provided that comprises a leading edge and an axially spaced-apart trailing edge, the leading edge having an axially-extending external surface curvature, a root and a tip spaced-apart along a radially-extending span axis, a pressure sidewall and a laterally-spaced-apart suction sidewall, a cooling circuit positioned between the pressure sidewall and the suction sidewall for channeling a fluid flow for cooling the airfoil. A plurality of cooling holes is formed in the leading edge along the span axis of the airfoil in fluid communication with the cooling circuit. At least some of the cooling holes have a diffuser section communicating with the leading edge surface. The diffuser section has opposed walls defining an exit opening on the surface of the leading edge and a respective cylindrical metering section positioned between and communicating with the interior of the airfoil and the diffuser section, wherein the diffuser section is formed by laser and the cylindrical metering section is formed by EDM.
Further aspects of the invention will appear when taken in conjunction with the following drawings, in which:
Referring now specifically to the drawings, examples of airfoils with leading edge cooling holes are shown in
Referring now to
In the exemplary embodiment illustrated in
The airfoil 32 includes a leading edge 36 and an opposite trailing edge 38. The airfoil 32 also includes a root 40 at a platform portion of the dovetail 34, and an opposite tip 42 spaced radially-apart along a generally radially-extending span axis.
The airfoil 32 also includes a pressure sidewall 44 that is generally concave and an opposite, suction sidewall 46 that is generally convex and is spaced-apart from the pressure sidewall 44. The pressure sidewall 44 and suction sidewall 46 extend from leading edge 36 to trailing edge 38, and root 40 to tip 42, respectively. Airfoil 32 as well as the dovetail 34 includes a cooling circuit or channel 50 disposed between the airfoil sides 44 and 46 for channeling the cooling fluid “F” through the airfoil for providing cooling during operation.
Although the specific airfoil 32 is shown as a portion of the turbine rotor blade 30, the invention applies as well to any form of airfoil such as those also found in the stationary turbine nozzle (not shown).
In accordance with one exemplary embodiment of the invention, a plurality of leading edge cooling holes 60 are spaced-apart along the leading edge 36 in three rows for discharging the cooling fluid “F” from the cooling circuit 50 inside the airfoil 32 along its outer surface to provide a cooling film of fluid onto the surface of the airfoil, particularly in the area of the leading edge 36 and areas immediately aft of the leading edge 36.
Referring now to
As is shown in
The advantages of this process include the fact that investment is minimized over an all EDM process because of increased throughput and the ability of a single laser machine to replace between 2 and 5 EDM machines. Overall part quality is improved by using the more precise laser process for the diffuser section 62 of the cooling holes 60 on the surface of the airfoil 32 where airflow disturbances are most likely to result in inefficient operation. The inner end of the pre-existing laser shaped diffuser section 62 can also serve as a locating guide for the EDM electrode as it drills the cylindrical metering section 64 through to the cooling circuit, minimizing scrap and rework.
The laser milling process can be altered via programming, eliminating the need for EDM electrode changes and EDM electrode tooling, which have a significant impact on investment amounts and manufacturing scheduling. The hybrid system utilizes transferable tooling between laser and EDM, minimizing setup and positioning errors when moving the part from one machine to the second machine.
An airfoil with cooling holes formed by a combination of laser and EDM and a related method are described above. Various details of the invention may be changed without departing from its scope. Furthermore, the foregoing description of the preferred embodiment of the invention and the best mode for practicing the invention are provided for the purpose of illustration only and not for the purpose of limitation—the invention being defined by the claims.
