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Pickling The Forgings
The forgings were then pickled in a hot solution of either ni...

Drop Forging Dies
The kind of steel used in the die of course influences the he...

Bessemer Process
The bessemer process consists of charging molten pig iron int...

Heat Treatment Of Axles
Parts of this general type should be heat-treated to show the...

Using Illuminating Gas
The choice of a carburizing furnace depends greatly on the fa...

Preventing Decarbonization Of Tool Steel
It is especially important to prevent decarbonization in such...

Effect Of A Small Amount Of Copper In Medium-carbon Steel
This shows the result of tests by C. R. Hayward and A. B. Joh...

Non-shrinking Oil-hardening Steels
Certain steels have a very low rate of expansion and contract...

A combination of the characteristics of nickel and the charac...

High-chromium Or Rust-proof Steel
High-chromium, or what is called stainless steel containing f...

Composition And Properties Of Steel
It is a remarkable fact that one can look through a dozen tex...

For Milling Cutters And Formed Tools
FORGING.--Forge as before.--ANNEALING.--Place the steel in a ...

The Packing Department
In Fig. 56 is shown the packing pots where the work is packe...

Impact Tests
Impact tests are of considerable importance as an indication ...

William Kelly's Air-boiling Process
An account of Bessemer's address to the British Association w...

This steel like any other steel when distorted by cold worki...

SILICON is a very widespread element (symbol Si), being an es...

Fatigue Tests
It has been known for fifty years that a beam or rod would fa...

A Satisfactory Luting Mixture
A mixture of fireclay and sand will be found very satisfactor...

Pyrometry And Pyrometers
A knowledge of the fundamental principles of pyrometry, or th...

Rate Of Cooling


At the option of the manufacturer, the above treatment of gear
forgings could be substituted by normalizing the forgings at a
temperature of from 1,550 to 1,600 deg.F. The most important criterion
for proper normalizing, consisted in allowing the forgings to cool
through the critical temperature of the steel, at a rate not to exceed
50 deg.F. per hour. For the two standard steels used, this consisted in
cooling from the normalizing temperature down to a temperature
of 1,100 deg.F., at the rate indicated. Forgings normalized in this
manner will show a Brinell hardness of from 177 to 217. The question
has been repeatedly asked as to which treatment will produce the
higher quality finished part. In answer to this I will state that
on simple forgings of comparatively small section, the normalizing
treatment will produce a finished part which is of equal quality to
that of the quenched and annealed forgings. However, in the case of
complex forgings, or those of large section, more uniform physical
properties of the finished part will be obtained by quenching and
annealing the forgings in the place of normalizing.

The heat treatment of the finished gears consisted of quenching
in oil from a temperature of from 1,420 to 1,440 deg.F. for the No.
X-3,340 steel, or from a temperature of from 1,500 to 1,540 deg.F.
for No. 6,140 steel, followed by tempering in saltpeter or in an
electric furnace at a temperature of from 650 to 700 deg.F.

The question has been asked by many engineers, why is the comparatively
low scleroscope hardness specified for gears? The reason for this is
that at best the life of an aviation engine is short, as compared with
that of an automobile, truck or tractor, and that shock resistance
is of vital importance. A sclerescope hardness of from 55 to 65
will give sufficient resistance to wear to prevent replacements
during the life of an aviation engine, while at the same time this
hardness produces approximately 50 per cent greater shock-resisting
properties to the gear. In the case of the automobile, truck or
tractor, resistance to wear is the main criterion and for that
reason the higher hardness is specified.

Great care should be taken in the design of an aviation engine
gear to eliminate sharp corners at the bottom of teeth as well
as in keyways. Any change of section in any stressed part of an
aviation engine must have a radius of at least 1/32 in. to give
proper shock and fatigue resistance. This fact has been demonstrated
many times during the Liberty engine program.

Next: Connecting Rods

Previous: Gears

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