Randolph C Helmink

6338189, Jan 15, 2002

Oct 7, 1999

09/414267

Raymond Ruiwen Xu - Carmel IN
Stephen N. Hammond - Brownsburg IN
Jacque B. Kennedy - Indianapolis IN
Randolph C. Helmink - Indianapolis IN
Robert A. Testin - Zionsville IN

Allison Engine Company, Inc. - Indianapolis IN

B23P 1700

29423, 29446, 723534

The present invention generally relates to an external cylindrical or conic section shaped fixture which is tightly fit around the same shaped workpiece prior to expansion forming to a final dimension. During expansion forming, the external fixture is also deformed and is therefore designed for one-time use. The external cylindrical or conic section shaped fixture of the present invention is particularly useful for expansion forming of workpieces which contain brazed lap joints. The external fixture restrains, out-of-plane joint rotation and reduces the stress concentrations existing near the lap joints. Additionally, the external fixture provides additional load carrying capability to allow better load distribution during expansion forming. No change is required to the expansion forming machinery or the inner expander dies (jaws) with use of the present invention. Because the external fixture fits tightly over the workpiece, applying a compressive force when the inner expander jaws expand during the forming process, the bending moment on the brazed lap joints is significantly reduced.

6551372, Apr 22, 2003

Sep 15, 2000

09/663025

Bruce A. Ewing - Martinsville IN
Sushil K. Jain - Indianapolis IN
Kenneth A. Green - Greenwood IN
Randolph C. Helmink - Indianapolis IN
Allister James - Orlando FL

Rolls-Royce Corporation - Indianapolis IN

C22C 3302

75246, 419 28, 419 29, 419 49, 419 48

A nickel base powder metallurgy superalloy gas turbine engine disk for a compressor or turbine. The wrought powder metallurgy gas turbine engine disk has desirable fatigue crack growth resistance and a superior balance of tensile, creep rupture and low cycle fatigue strength characteristics. In one embodiment the disk defines a segregation free homogenous structure.

8215181, Jul 10, 2012

Sep 3, 2009

12/553209

Randolph Clifford Helmink - Avon IN, US

Rolls-Royce North American Technologies, Inc. - Indianapolis IN

G01N 3/02

73827, 73760

The present invention provides a test specimen configured for mechanical load life characterization testing of a dual wall bonded airfoil for use in a turbomachinery device. The dual wall bonded airfoil has a spar and a skin bonded to the spar. The test specimen includes a main stress body, which includes a test spar component configured to represent the spar of the dual wall bonded airfoil; a test skin component configured to represent the skin of the dual wall bonded airfoil; and a test bond joint bonding the skin component to the spar component. The test bond joint is configured to represent the actual bond joint between the spar and the skin of the dual wall bonded airfoil. The test specimen is structured to simulate the dual wall bonded airfoil for testing in a mechanical testing machine.

20100252151, Oct 7, 2010

Apr 6, 2010

12/755170

David U. Furrer - Brownsburg IN, US
Randolph C. Helmink - Avon IN, US

Rolls-Royce Corp. - Indianapolis IN

C21D 1/00
C22F 1/00

148714

A heat treatment technique may include heating an alloy component to a temperature above a transition temperature of the alloy or heating an alloy component to a temperature below the transition temperature of the alloy. The heat treatment technique further may include cooling a first portion of the alloy component at a first cooling rate, and cooling a second portion of the alloy component at a second cooling rate different than the first rate. The first cooling rate may result in formation of a plurality of first precipitate phase domains comprising a first average size in the first portion, and the second cooling rate may result in formation of a plurality of second precipitate phase domains comprising a second average size in the second portion. The average size of the first precipitate phase domains may be different than the average size of the second precipitate phase domains.

20120222961, Sep 6, 2012

Dec 28, 2011

13/338811

Michel Shawn Smallwood - Greenwood IN, US
Tab Michael Heffernan - Plainfield IN, US
Mark Steven McCormick - Martinsville IN, US
Randolph Clifford Helmink - Avon IN, US
Matthew Kush - Martinsville IN, US

C23C 28/00
C25D 17/00

205187, 204242

A method includes removing a casting shell and core from a cast component, which may be a gas turbine blade. The method further includes utilizing a focused removal technique, such as a water jet or laser drill, to remove a portion of a virtual pattern cast (VPC) shell from the cast component. The cast component is then exposed to a leaching solution and high pressure water wash to remove an internal core material and a portion of the VPC shell remainder from the cast component. The method further includes exposing the cast component to a high agitation leaching solution and to the high pressure water wash for a minimal time. An electroless nickel-boron coating is then applied to the cast component, and an electrolytic palladium coating is further applied to the cast component. The cast component is further exposed to a high agitation leaching solution for an extended period.

46801600, Jul 14, 1987

Dec 11, 1985

6/807943

Randolph C. Helmink - Indianapolis IN

TRW Inc. - Cleveland OH

B22F 700

419 6

An improved method of forming a rotor includes the steps of hot isostatically pressing powdered metal to form disc-shaped hub sections. Each of the hub sections has a rim portion with a relatively large or coarse grain size to optimize high temperature creep properties. The central portion of each hub section has a relatively small or fine grain size to optimize tensile strength and reduce cycle fatigue at intermediate temperatures. Dispersion of any defects in the hub sections is promoted by plastically deforming the hub sections. Preformed blades are placed in an annular array between a pair of the hub sections and the hub sections are bonded together to interconnect the blades and hub sections.

20160215369, Jul 28, 2016

Aug 11, 2014

14/456424

- Indianapolis IN, US
Randolph C. HELMINK - Avon IN, US

C22C 19/05

Nickel-base composite niobium bearing alloys including delta and/or eta strengthening phases in addition to gamma prime precipitates in a gamma matrix.

20150259787, Sep 17, 2015

Mar 9, 2015

14/642127

- Indianapolis IN, US
Ann Bolcavage - Indianapolis IN, US
Randolph C. Helmink - Avon IN, US

C23C 14/34
C25D 5/48
C23C 16/24
C23C 16/06
C23C 16/50
C23C 16/40

In some examples, an article may include a superalloy substrate and a coating on the superalloy substrate. In accordance with this example, the coating includes a diffusion barrier layer on the substrate and a wear resistant oxide layer over the diffusion barrier layer. The diffusion barrier layer may include iridium and the wear resistant oxide layer may include at least one of silica, zirconia, or chromia.