Abrading – Abrading process
Reexamination Certificate
2001-12-13
2003-05-27
Morgan, Eileen P. (Department: 3723)
Abrading
Abrading process
C451S365000, C451S408000, C269S238000
Reexamination Certificate
active
06568993
ABSTRACT:
This invention relates to fixturing to support a gas turbine component, and more specifically, to clamping the gas turbine component in the fixture and shaping the root of the gas turbine component.
BACKGROUND OF THE INVENTION
In the most commonly practiced approach, turbine blades for gas turbine engines are cast to approximately the final shape. Then portions of the turbine blade, such as the root and the shroud, if any, are shaped to the final desired form by a technique such as grinding. The turbine blade is thereafter processed by depositing protective coatings or by other procedures.
The finished turbine blades are assembled into a turbine disk or wheel, with a “dovetail” form on the root of each turbine blade engaging a respective conformably shaped slot on the turbine disk. The turbine disk is in turn supported on a shaft in the gas turbine engine. The turbine blades must have precisely established positions and angular orientations in the turbine disk. Any mispositioning and misorientation may lead to aerodynamic inefficiency and the introduction of unacceptable vibrations in the turbine disk and the turbine blade as the turbine disk turns during service.
Because it is the root of each turbine blade that engages the slot on the turbine disk, the root must be shaped very precisely. Two techniques have been widely used to hold the turbine blade in an exact location and orientation for the shaping of the root. In one, the airfoil of the turbine blade is cast into a matrix of a metal with a low melting point, which is used to hold the turbine blade with its root positioned for grinding or other shaping. This approach, while operable, requires that the low-melting-point metal be cleaned from the surface of the airfoil after the shaping of the root is completed. Even traces of the metal remaining after careful cleaning of the surface of the airfoil may adversely affect the subsequent application of the coatings. Mechanical fixtures or jigs have been developed to hold the turbine blade. These fixtures avoid the use of the low-melting-point metal, but have not been fully satisfactory because they misposition the root or because they do not hold the turbine blades sufficiently repeatably and securely so that each root is shaped the same.
There is a need for an improved approach to the shaping of the roots of turbine blades and other gas turbine components. The present invention fulfills this need, and further provides related advantages.
SUMMARY OF THE INVENTION
The present invention provides a fixture for holding a gas turbine component, such as a turbine blade, a compressor blade, or some types of vanes, in a specific fixed position for the shaping of the gas turbine component, and a method for performing the shaping. The approach does not use a molten metal whose complete removal is difficult. The fixture holds the gas turbine component using features of the gas turbine component that have been previously precisely established. This approach allows each gas turbine component to be processed precisely, quickly, reproducibly, without contamination, and with minimal dependence upon operator skill.
A fixture is provided for clamping a gas turbine component, such as a turbine blade, having a component longitudinal axis. The turbine component has a root having a root surface including a first pair of first pressure surfaces on either side of the component longitudinal axis and oriented at a first, preferably acute angle to the component longitudinal axis, a second pair of second pressure surfaces on either side of the component longitudinal axis and oriented at a second, preferably obtuse, angle to the component longitudinal axis, and a tang at an end of the root. The fixture comprises a base upon which the remainder of the fixture is supported, and a stop which prevents the gas turbine component moving past a stop limit when the gas turbine component is forced in a clamping direction parallel to the component longitudinal axis. The fixture further comprises two clamp arms, a first clamp arm on a leading-edge side of the gas turbine component with a first clamp surface facing the gas turbine component, and a second clamp arm on a trailing-edge side of the gas turbine component with a second clamp surface facing the gas turbine component. Each clamp arm is movable, preferably by a pivoting movement, between a released position in which its clamp surface does not contact one of the pressure surfaces and a clamped position in which its clamp surface contacts one of the pressure surfaces and forces the gas turbine component in the clamping direction and against the stop. A clamping force source, preferably an hydraulic cylinder, controllably moves each of the clamp arms between the released position and the clamped position.
Preferably, the first pair of first pressure surfaces engage the stop and the second pair of second pressure surfaces are contacted by the respective clamp surfaces. The stop is desirably in the form of a shoulder. Each clamp surface may be conformably shaped to the pressure surface that is contacted by the clamp surface when the clamp arm is in the clamped position.
A method for shaping a gas turbine component comprises the steps of furnishing the gas turbine component, as described above, and a fixture, as described above in its basic or modified forms. The gas turbine component is clamped in the fixture, and thereafter the root of the gas turbine component is shaped while the gas turbine component is clamped into the fixture. Preferably, the tang portion of the root is shaped by grinding. The end surfaces of the root may also be shaped, preferably by grinding.
The present-approach provides a convenient fixturing approach which avoids the use of molten metal and also ensures that the gas turbine component is properly and securely positioned for shaping of the root, particularly the tang of the root.
Other features and advantages of the present invention will be apparent from the following more detailed description of the preferred embodiment, taken in conjunction with the accompanying drawings, which illustrate, by way of example, the principles of the invention. The scope of the invention is not, however, limited to this preferred embodiment.
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Jones Daniel Edward
Juneau, Jr. Jacques
Garmong Gregory O.
General Electric Company
Morgan Eileen P.
Ramaswamy V. G.
Shakeri Hadi
LandOfFree
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