Measuring and testing – Wind tunnel: aerodynamic wing and propeller study
Reexamination Certificate
2003-03-26
2004-08-10
Williams, Hezron (Department: 2856)
Measuring and testing
Wind tunnel: aerodynamic wing and propeller study
C073S148000, C073S170070, C073S170090, C073S170110, C073S861660
Reexamination Certificate
active
06772627
ABSTRACT:
FIELD OF THE INVENTION
The present invention relates to improved apparatus and methods for airflow testing, and more particularly to measurement of airflow characteristics of a gas path component of a gas turbine engine.
BACKGROUND OF THE INVENTION
Devices such as natural gas compressors, air compressors, steam turbines, and gas turbines, include various internal components, such as vanes, stators, blades, diffusers, housings, and combustors though which quantities of air, natural gas, steam, or combusted gas flow. It is important to the proper operation of these devices that these internal components modify the internal flow in the correct way. These modifications include changing the average properties of the flowing medium (such as pressure, temperature, density, velocity, etc.) and/or the profiles and gradients of these properties.
These internal components are designed to change the properties of the flowing medium within the context of the device, i.e., change the properties in respect to internal devices either upstream or downstream of the particular component. For example, the first stage turbine vane of a gas turbine engine receives combusted air from a combustor and provides the combusted air to turbine blades located downstream.
This interaction between internal components is often a function of the radial and circumferential extent of the component's flow path. For example, a turbine vane includes a portion of a flow path near the hub (inner most lower wall) of the vane and the outer diameter (outer most wall) of the vane. It is typical that components such as turbine vanes provide air in velocity and pressure gradients that change from the inner hub to the outer diameter. Further, these property gradients of the gas change circumferentially, i.e., the gradient closest to the trailing edge of the vane can be different than the gradients at a position in between adjacent trailing edges.
As vanes are manufactured, there are times when the trailing edge of the vane is bent manually. Further, it is possible that the trailing edge of the vane, or other geometrical aspects of the vane, is altered as a result of long-term usage. In either of these situations, the gas property gradients from the exit of the vane are altered. However, there may not be suitable test equipment for characterizing the modified gradients. One simple attempt to provide such information involves the use of a protractor with a single inner foil rotatably coupled to the protractor. As air from a tested component flows across this assembly, the angle of the airfoil changes, similar in operation to a weather vane.
What is needed is an improvement in airflow testing that improves the accuracy with which the flow characteristics of the component are determined. The present invention does this in a novel and nonobvious manner.
SUMMARY OF THE INVENTION
The present invention relates to various apparatus and methods for airflow testing of a component of a gas turbine engine.
One embodiment of the present invention includes an apparatus for flow testing of gas through a component. The apparatus includes a test bench including a source of flowing gas and configured to mount the component proximate to the aperture. The apparatus includes a measurement section with an arc-shaped inner flowpath and an arc-shaped outer flowpath for receiving therebetween the gas exiting the component. The measurement section including a measurement device between the inner flowpath and the outer flowpath that is being rotatable about a centerline.
Another embodiment of the present invention includes an apparatus for flow testing of gas through a component. The apparatus includes a test bench including a source of flowing gas and a housing adapted and configured to mount the component proximate to the aperture. The apparatus includes a measurement section located downstream of and proximate to the aperture including at least two circumferentially spaced-apart measurement devices each providing a signal in response to the flow of gas proximate thereto, and each measurement device having a different length in the radial direction.
Another embodiment of the present invention includes an apparatus for flow testing of gas through a component. The apparatus includes means for simultaneously measuring properties of the gas exiting from the component at a plurality of radial locations and a plurality of circumferential locations, said measuring means being rotatable transverse to the flowpath of the component.
Another embodiment of the present invention includes a method for evaluating a gasflow characteristic of a gaspath component for a gas turbine engine. The method includes mounting the component, placing a measurement device at a first location downstream of the component; making a first measurement of a property of the gas with the measurement device placed at the first location, moving the measurement device to a second location downstream of the component; and making a second measurement of a property of the gas with the measurement device placed at the second location;
Another embodiment of the present invention includes a method for evaluating a gasflow characteristic of a gaspath component for a gas turbine engine. The method includes mounting the component in a first flow direction, directing a flow of the gas into the component, making a first measurement of a property of the gas with the component mounted in the first flow direction, mounting the component in a second flow direction to the support member, the second flow direction being opposite of the first direction; and making a second measurement of a property of the gas with the component mounted in the second flow direction.
Yet other aspects of the present invention will be apparent from the description of the preferred embodiment, the drawings, and the claims to follow.
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Rogers David A.
Williams Hezron
Woodard Emhardt Moriarty McNett & Henry LLP
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