Components with cooling channels formed in coating and methods of manufacture
A coating and component technology, applied in the field of gas turbine engines, can solve the problems of reduced strength and reduced wall thickness of cast airfoils
Inactive Publication Date: 2012-09-26
GENERAL ELECTRIC CO
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Problems solved by technology
However, the reduction in wall thickness and the corresponding reduction in strength of cast airfoils still presents concerns for these techniques as the channels are machined into the load bearing substrate
Method used
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[0046] The terms "first", "second", etc. herein do not denote any order, number or importance, but are used to distinguish one element from another. The terms "a" and "an" herein do not denote a limitation of quantity, but mean that there is at least one of the referenced item. The modifier "about" used in connection with a quantity is inclusive of the stated value and has the meaning dictated by the context (eg, includes the degree of error associated with measurement of the particular quantity). Additionally, the term "combination" includes blends, mixtures, alloys, reaction products, and the like.
[0047] Furthermore, in this specification, the word "(s)" is generally intended to include both the singular and the plural of the term it modifies, thereby including one or more of that item (e.g., "via" may include one or more multi-access holes unless otherwise specified). Reference throughout the specification to "one embodiment," "another embodiment," "an embodiment," etc...
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Abstract
A method of fabricating a component is provided. The method includes depositing a structural coating on an outer surface of a substrate, where the substrate has at least one hollow interior space. The method further includes forming one or more grooves in the structural coating. Each groove has a base and extends at least partially along the substrate. The method further includes depositing at least one additional coating over the structural coating and over the groove(s), such that the groove(s) and the additional coating together define one or more channels for cooling the component. The method further includes forming one or more access holes through the base of a respective groove, to connect the respective groove in fluid communication with the respective hollow interior space, and forming at least one exit hole through the additional coating for each channel, to receive and discharge coolant from the respective channel. A component with cooling channels formed in a structural coating is also provided.
Description
technical field [0001] The present invention relates generally to gas turbine engines, and more particularly to microchannel cooling therein. Background technique [0002] In a gas turbine engine, air is pressurized in a compressor and mixed with fuel in a combustor to produce hot combustion gases. Energy is extracted from gases in a high pressure turbine (HPT) driving a compressor and a low pressure turbine (LPT) driving a fan in turbofan aircraft engine applications or an external shaft for marine and industrial applications. [0003] Engine efficiency increases with the temperature of the combustion gases. However, the combustion gases heat various components along their flow paths, which in turn requires cooling of these components to achieve long engine life. Typically, the hot gas path components are cooled by bleed air from the compressor. This cooling process reduces engine efficiency because the bleed air is not used for the combustion process. [0004] Gas turb...
Claims
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IPC IPC(8): F01D25/12F02C7/12C23C4/12C23C14/24C23C26/00
CPCY02T50/672F01D5/18F05D2230/14F05D2230/13F05D2230/30Y02T50/676Y02T50/60Y10T29/49982Y10T29/49984
Inventor R·S·班克D·M·利普金魏斌
Owner GENERAL ELECTRIC CO