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Technical Briefs

High-Pressure Angle Gears: Comparison to Typical Gear Designs

[+] Author and Article Information
Robert F. Handschuh

Andrew J. Zakrajsek

 NASA Glenn Research Center, Cleveland, OH 44135azakrajs@gmail.com

J. Mech. Des 133(11), 114501 (Nov 11, 2011) (6 pages) doi:10.1115/1.4004458 History: Received June 03, 2010; Revised April 06, 2011; Published November 11, 2011; Online November 11, 2011

A preliminary study has been completed to determine the feasibility of using high-pressure angle gears in aeronautic and space applications. Tests were conducted in the NASA GRC Spur Gear Test Facility at speeds up to 10,000 rpm and 73 N m (648 in. lb) for 3.18, 2.12, and 1.59 module gears (8, 12, and 16 diametral pitch gears), all designed to operate in the same test facility. The 3.18 module (8-diametral pitch), 28 tooth, 20 deg pressure angle gears are the NASA GRC baseline test specimen. Also, 2.12 module (12-diametral pitch), 42 tooth, 25 deg pressure angle gears were tested. Finally, 1.59 module (16-diametral pitch), 56 tooth, 35 deg pressure angle gears were tested. The high-pressure angle gears were the most efficient when operated in the high-speed aerospace mode (10,000 rpm, lubricated with a synthetic turbine engine oil) and produced the lowest wear rates when tested with a perfluoroether-based grease. The grease tests were conducted at 150 rpm and 71 N m (630 in. lb).

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Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 10

Grease retention shroud cad model

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Figure 9

Left—20 deg pressure angle gear (3.18 module (8 Pitch)). Right—High-pressure angle gear 1.59 module (16 Pitch).

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Figure 8

Top—shows rust forming on the gear profile. Bottom—shows rust debris from metal-on-metal contact. (Both photographs from a 2.12 module (12-diametral pitch) gear test)

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Figure 7

Photograph of HPA gear flank end chip

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Figure 6

Photograph of HPA gears after testing

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Figure 5

Photograph of HPA gears before testing

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Figure 4

Temperature results for three different gearing configurations. All tests conducted at 10,000 rpm, 71 N m (630 in. lb). Flow rate at 40 psi ∼ 8.1 ml/s (0.13 gpm).

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Figure 3

Test facility at NASA Glenn Research Center

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Figure 2

Left to right; 3.18, 2.12, and 1.59 module (8, 12, and 16 diametral pitch) test gears

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Figure 1

Effect of gear design on sliding velocity at any point along the line of action between 3.18 and 1.59 module (8 and 16 diametral pitch) gears for a 1:1 ratio

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Figure 11

Shrouds on the high-pressure angle gears during tests

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