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Cooling channel for airfoil near-wall leading edge

A technology for cooling channels and airfoils, applied in the field of turbine airfoils

Pending Publication Date: 2022-03-01
POWER SYST MFG LLC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, cooling must occur in an efficient manner in order to use the cooling fluid effectively

Method used

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  • Cooling channel for airfoil near-wall leading edge
  • Cooling channel for airfoil near-wall leading edge
  • Cooling channel for airfoil near-wall leading edge

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Embodiment Construction

[0024] At a high level, the subject matter of the present application generally relates to an airfoil for a gas turbine including a cooling circuit integrated in various configurations. The airfoil may generally include an airfoil wall having an inner surface and an outer surface at least partially enclosing the airfoil chamber. The cooling circuits may be formed in various locations in the airfoil wall to provide enhanced heat transfer from the airfoil when the gas turbine is in operation and as cooling fluid or gas passes through the cooling circuits. For turbine hardware operating in harsh environments, fully consider using this airfoil cooling technology to accommodate additional components such as OD and ID platforms, air shields on the outside or inside of the airfoil, or alternative high temperature turbine components.

[0025] Referring now to FIG. 1A , a gas turbine airfoil 100 is provided. The turbine airfoil 100 includes a bottom portion, commonly referred to as a ...

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Abstract

An airfoil, a gas turbine engine assembly including such an airfoil, and a method of manufacturing the same. The airfoil includes a plurality of cooling channels proximate a leading edge of the airfoil, each cooling channel including an inlet disposed on an inner surface of the airfoil of one of the pressure side wall and the suction side wall and an outlet disposed on an outer surface of the airfoil of the other of the pressure side wall and the suction side wall. The cooling channels are arranged in a staggered configuration such that an alternating pattern of cooling fluid flow is provided at the airfoil leading edge near the stagnation point of the airfoil.

Description

[0001] Cross References to Related Applications [0002] This patent application claims priority to U.S. Patent Application Serial No. 16 / 417,006, filed May 20, 2019, the entire disclosure of which is incorporated herein by reference. technical field [0003] The present invention relates to turbine airfoils, and more particularly, to cooling circuits incorporated into turbine airfoils. Background technique [0004] A typical gas turbine engine consists of three main sections: a compressor section, a combustor section, and a turbine section. During a standard operating cycle, the compressor section is used to pressurize the air supplied to the combustor section. In the combustor section, fuel is mixed with compressed air from the compressor section and ignited to produce high temperature and high velocity combustion gases. These combustion gases then flow into a multi-stage turbine where the hot gases flow over alternating rows of rotating and stationary gas turbine airfoi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18
CPCF01D5/18F01D5/186F05D2240/121F05D2240/123F05D2250/18F05D2260/202F05D2260/204F01D5/187F05D2230/31B33Y80/00
Inventor G·E·沃格尔V·基塔戈罗德
Owner POWER SYST MFG LLC
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