Systems and methods for producing one or more cooling holes in an airfoil for a gas turbine engine

a gas turbine engine and cooling hole technology, which is applied in the direction of turbines, machines/engines, mechanical equipment, etc., can solve the problem of difficulty in drilling holes into the airfoil at such a shallow angl

Inactive Publication Date: 2019-03-28
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

Enables the efficient production of cooling holes at a relatively steep angle, improving access and ensuring effective airflow through the airfoil, while maintaining a smooth surface by removing the hole starter bosses and sealing access holes.

Problems solved by technology

It can be very difficult to drill holes into the airfoil at such a shallow angle.

Method used

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  • Systems and methods for producing one or more cooling holes in an airfoil for a gas turbine engine
  • Systems and methods for producing one or more cooling holes in an airfoil for a gas turbine engine
  • Systems and methods for producing one or more cooling holes in an airfoil for a gas turbine engine

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Embodiment Construction

[0015]Illustrative embodiments will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all embodiments are shown. The disclosure may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Like numbers refer to like elements throughout.

[0016]Illustrative embodiments of the disclosure are directed to, among other things, systems and methods for producing one or more cooling holes in an airfoil for a gas turbine engine. In some instances, one or more hole starter bosses may be cast on a suction side, a pressure side, or both of the airfoil. Using the hole starter bosses as a guide, the cooling holes may be drilled into the surface of the suction side or the pressure side of the airfoil. The starter bosses may enable a relatively steep drill angle into the surface of the airfoil. After the cooling holes have been drilled into the surface of the airfoil, the hole starter boss...

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Abstract

A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.

Description

CROSS-REFERENCE TO RELATED APPLICATIONS[0001]The disclosure claims priority to, the benefit of, and is a divisional application of U.S. patent application Ser. No. 14 / 950,081, filed Nov. 24, 2015, now U.S. Pat. No. ______, which is hereby incorporated herein in its entirety by reference.FIELD[0002]Embodiments of the disclosure relate generally to gas turbine engines and more particularly relate to systems and methods for producing one or more cooling holes in an airfoil for a gas turbine engine.BACKGROUND[0003]In some instances, buckets may be cooled with radial holes that exit (or break out) on a surface of the airfoil rather than running the full length of the airfoil and emerging at the tip. Such cooling holes may break out of the airfoil in the shape of a long, narrow, ellipse. It can be very difficult to drill holes into the airfoil at such a shallow angle.BRIEF DESCRIPTION[0004]Some or all of the above needs and / or problems may be addressed by certain embodiments of the disclo...

Claims

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Application Information

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Patent Type & AuthorityApplications(United States)
IPC IPC(8): F01D5/18F01D5/00F01D5/22
CPCF05D2230/80F01D5/18F05D2220/32F05D2230/10F05D2260/20F05D2230/21F01D5/186F05D2240/305F05D2240/306F05D2260/202F05D2230/11F05D2230/14F05D2250/52F01D5/005B23B2215/81F01D5/225B23P15/00
InventorJACALA, ARIEL CAESAR PREPENAWILLETT, JR., FRED THOMAS
OwnerGENERAL ELECTRIC CO