Abstract:
A method for thermally imaging a moving workpiece of a gas turbine engine comprises identifying a plurality of geometric features to construct a composite image. The geometric features include at least one integral thermal feature of the moving workpiece, and at least one artificial feature applied to the workpiece for diagnostic purposes. One of the plurality of geometric features is identified as a master feature, and the remainder of the plurality of geometric features are located relative to the master feature with relative actual coordinates. A pixel location of the master feature is identified or each image, and the remainder of the plurality of geometric features are located relative to the master feature with relative pixel coordinates. Offset, rotation, and scaling of the secondary images are varied to minimize a relative difference between the relative pixel coordinates and the relative actual coordinates. The offset, rotated, and scaled secondary images are combined with the reference image to form a composite image.
Abstract:
A self-cooled orifice structure, that may be for a combustor of a gas turbine engine includes a hot side panel, a cold side panel spaced from the hot side panel, and a continuous first wall extending axially between the hot and cold side panels and spaced radially outward from a centerline. The structure may further include a first plurality of helical vanes projecting laterally, radially, inward from the first wall for flowing cooling air in a spiraling fashion through the cold side panel, then through the hot side panel.
Abstract:
A turbine engine system includes a heat source, a heat exchanger, a cooling medium inlet and a cooling medium outlet. The heat source includes a first passage. The heat exchanger includes a second passage and a third passage. The first and the second passages are configured in a closed loop circuit. The third passage is configured between the inlet and the outlet in an open loop circuit.
Abstract:
A method for thermally imaging a moving workpiece of a gas turbine engine using long wavelength infrared (LWIR) images of the workpiece captured during operation of the gas turbine engine. The method comprises determining average pixel intensity and pixel variation in intensity for each pixel across the plurality of LWIR images, determining average area intensity and area variation in intensity across a range of areas defined by increasing length scales about a selected pixel, and identifying as a critical length scale a length scale at which area variation in intensity is minimized as a function of length scale, for which the area intensity remains substantially the same as the average pixel intensity of the selected pixel. A composite image is built such that each pixel of the composite image has intensity equal to an average area intensity centered on that pixel, over the critical length scale.
Abstract:
A turbine section includes a rotor assembly which includes an internal cooling passage. A segmented seal is adjacent the rotor assembly and includes a fluid passage that is in fluid communication with the internal cooling passage.
Abstract:
A seal assembly that may be for turbine engine includes a first wall defining in-part a first flowpath and a second wall defining in-part a second flowpath having a pressure that is greater than the first flowpath. The second wall has a plurality of metering apertures in fluid communication between the second flowpath and a cavity defined by and between the first and second walls. The walls may be convoluted and generally, resiliently compressed between two substantially opposing surfaces for providing a seal between the two flowpaths.
Abstract:
A method for thermally imaging a moving workpiece of a gas turbine engine using long wavelength infrared (LWIR) images of the workpiece captured during operation of the gas turbine engine. The method comprises determining average pixel intensity and pixel variation in intensity for each pixel across the plurality of LWIR images, determining average area intensity and area variation in intensity across a range of areas defined by increasing length scales about a selected pixel, and identifying as a critical length scale a length scale at which area variation in intensity is minimized as a function of length scale, for which the area intensity remains substantially the same as the average pixel intensity of the selected pixel. A composite image is built such that each pixel of the composite image has intensity equal to an average area intensity centered on that pixel, over the critical length scale.
Abstract:
A method for thermally imaging a moving workpiece of a gas turbine engine comprises identifying a plurality of geometric features to construct a composite image. The geometric features include at least one integral thermal feature of the moving workpiece, and at least one artificial feature applied to the workpiece for diagnostic purposes. One of the plurality of geometric features is identified as a master feature, and the remainder of the plurality of geometric features are located relative to the master feature with relative actual coordinates. A pixel location of the master feature is identified or each image, and the remainder of the plurality of geometric features are located relative to the master feature with relative pixel coordinates. Offset, rotation, and scaling of the secondary images are varied to minimize a relative difference between the relative pixel coordinates and the relative actual coordinates. The offset, rotated, and scaled secondary images are combined with the reference image to form a composite image.
Abstract:
A gas turbine engine includes a rotor carrying a blade, a ceramic vane adjacent the blade, a seal carried on the rotor adjacent the tip of the ceramic vane, and a cooling passage circuit extending through the blade, the seal, and the ceramic vane. The cooling passage circuit is configured to provide cooling air into the blade, then from the blade into the seal, and then from the seal into the ceramic vane.
Abstract:
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal plate includes a cooling passageway having a circumferentially-extending section radially aligned with the contact area.