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Surface Finishing for Additive Manufacturing

A technology for additive manufacturing and surface finishing, applied in additive manufacturing, engine manufacturing, process efficiency improvement, etc., which can solve problems such as reliability, accuracy and cost constraints

Active Publication Date: 2019-12-17
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Optimization of features such as these is currently limited by the reliability, precision and cost of conventional manufacturing methods / tooling

Method used

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  • Surface Finishing for Additive Manufacturing
  • Surface Finishing for Additive Manufacturing
  • Surface Finishing for Additive Manufacturing

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0036] figure 1 A gas turbine engine 20 is shown schematically. The gas turbine engine 20 disclosed herein is a twin rotor turbofan engine that generally includes a fan section 22 , a compressor section 24 , a combustor section 26 , and a turbine section 28 . Fan section 22 drives air along the bypass and core flow paths. Compressor section 24 compresses air along a core flow path for delivery into combustor section 26 for expansion via turbine section 28 . Although shown with a turbofan engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with a turbofan engine, as the teachings can be applied to other types of turbine engines, such as turbojet engine, turboshaft and three-rotor (plus fan) turbofan.

[0037] Engine 20 generally includes a lower rotor 30 and an upper rotor 32 mounted for rotation about a central engine longitudinal axis A relative to a stationary engine structure 36 . The lower r...

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PUM

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Abstract

The present invention relates to surface finishing for additive manufacturing. Specifically, an additively manufactured part includes heat transfer enhancing features having a surface finish of between about 125-900 microinches.

Description

technical field [0001] The present disclosure relates to gas turbine engines, and more particularly to additive manufacturing control of surface finishes for gas turbine engines. Background technique [0002] Gas turbine engines, such as those that power modern commercial and military aircraft, typically include a compressor section that compresses a stream of air, a combustor section that burns hydrocarbon fuel in the presence of the compressed air, and combustion The turbine section from which energy is extracted from the gas. [0003] Burners are exposed to high thermal loads for a long time. In the past, combustors have implemented various cooling arrangements to cool the combustor liner assembly. These cooling arrangements include a double wall assembly approach where the lining panel directly adjacent to the combustion gases is cooled by impingement cooling on the back side and film cooling on the gas side to maintain the temperature within material limits. [0004]...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/60F02C3/14
CPCF28F3/04F28F13/185F05B2230/30F28F2260/00F05D2230/30B22F5/009F23R3/002F23R2900/03044F28F2255/18F23R2900/00018F23R2900/03042Y02P10/25Y02T50/60B22F10/28B22F10/66B22F10/25
Inventor J·奥特S·J·芬克R·O·科菲S·斯滕平斯基J·J·小拉普L·道托瓦D·M·穆拉
Owner UNITED TECH CORP