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Rolf R Hetico

from Montgomery, OH
Age ~67
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Also known as:
Rolf R Retico
Phone and address:
10656 Indian Woods Dr, Cincinnati, OH 45242
(513) 247-0455
Related to:
Lon GerringLori Gerring, 69
Connected to:
Janelle L Hetisimer, 57Larry L Hetisimer, 74Holly H Hetke, 69Lisa N Hetke, 40Richard L Hetke, 72Clifton J Hetkes, 62Ryan P Hetkowski, 36Jessica R Hetlage, 35Judith D Hetlage, 65Aleksander Hetland, 42

Rolf Hetico Phones & Addresses

  • 10656 Indian Woods Dr, Montgomery, OH 45242 (513) 247-0455
  • Cincinnati, OH

Work

Company: Ge aviation, engineering Sep 2011 Address: Cincinnati Area Position: General manager, advanced components and manufacturing sciences

Education

Degree: B.S. School / High School: University of Cincinnati Specialities: Aerospace Engineering

Skills

Engineering • Aviation

Emails

l***[email protected]

Industries

Aviation & Aerospace

Resumes

Resumes

Rolf Hetico Photo 1

General Manager, Ge9X Engineering

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Location:
Cincinnati, OH
Industry:
Aviation & Aerospace
Work:
GE Aviation, Engineering - Cincinnati Area since Sep 2011
General Manager, Advanced Components and Manufacturing Sciences
Education:
University of Cincinnati
B.S., Aerospace Engineering University of Cincinnati
M.S., Engineering
Skills:
Engineering
Aviation

Publications

Us Patents

Non-Integral Fan Platform

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US Patent:
6447250, Sep 10, 2002
Filed:
Nov 27, 2000
Appl. No.:
09/723108
Inventors:
Sean Joel Corrigan - Fairfield OH
Jeffrey Clayton Potter - Holland MI
Joseph Timothy Stevenson - Amelia OH
Jay L. Cornell - Hamilton OH
James Michael Forrester - Springboro OH
Rolf Robert Hetico - Cincinnati OH
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 522
US Classification:
416193A, 416219 R, 416245 R, 416248
Abstract:
A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to a forward extension of the disk at a location between a tip and an axially aft spinner end of the spinner. Non-integral platforms circumferentially disposed between the fan blades. A booster spool is connected to the rotor disk by a mounting plate therebetween and the platforms are radially retained to the disk and mounting plates by pins through holes in mounting lugs depending radially inwardly from the platforms. Pairs of circumferentially oppositely facing retaining slots have retainers disposed therein which extend across the dovetail slots to axially retain the dovetail roots in the dovetail slots.

Methods And Apparatus For Structurally Supporting Airfoil Tips

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US Patent:
6779979, Aug 24, 2004
Filed:
Apr 23, 2003
Appl. No.:
10/421286
Inventors:
Aspi R. Wadia - Loveland OH
Rolf Hetico - Cincinnati OH
Robert Bruce Dickman - Cincinnati OH
Hsin-Yi Yen - Mason OH
Peter Wood - Loveland OH
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 510
US Classification:
416236R, 416500
Abstract:
An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip, a first side wall that extends in radial span between an airfoil root and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib that extends outwardly from at least one of the first side wall and the second side wall, such that a natural frequency of chordwise vibration of the airfoil is increased to a frequency that is not present within the gas turbine engine during engine operations.

Methods And Apparatus For Reducing Flow Across Compressor Airfoil Tips

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US Patent:
7270519, Sep 18, 2007
Filed:
Nov 12, 2002
Appl. No.:
10/292250
Inventors:
Aspi R. Wadia - Loveland OH, US
Rolf Hetico - Cincinnati OH, US
Robert Bruce Dickman - Cincinnati OH, US
Hsin-Yi Yen - Fairfield OH, US
Peter Wood - Loveland OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 5/10
US Classification:
416236R, 416235, 298897
Abstract:
An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip, a first side wall that extends in radial span between an airfoil root and the tip, wherein the first side wall defines a first side of said airfoil, and a second side wall connected to the first side wall at the leading edge and the trailing edge, wherein the second side wall extends in radial span between the airfoil root and the tip, such that the second side wall defines a second side of the airfoil. The airfoil also includes a rib extending outwardly from at least one of the first side wall and the second side wall, wherein the rib is configured to reduce airflow spillage past the tip.

Shrouded Turbofan Bleed Duct

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US Patent:
7607308, Oct 27, 2009
Filed:
Dec 8, 2005
Appl. No.:
11/297698
Inventors:
Robert Eugene Kraft - Cincinnati OH, US
Nelson Dirk Gibbens - Mason OH, US
Rolf Robert Hetico - Cincinnati OH, US
William Charles Groll - North Bend OH, US
William Andrew Bailey - Cincinnati OH, US
James Edward Stoker - Milford OH, US
Assignee:
General Electric Company - Schenectady NY
International Classification:
F02C 6/04
US Classification:
60785, 60795, 602261
Abstract:
A bleed duct is configured for bleeding fan air from the fan bypass duct in a turbofan aircraft engine. The bleed duct includes a tubular conduit having an inlet and outlet at opposite ends. The conduit is configured in flow area for recovering pressure from speeding fan air bled therethrough. A shroud extends forwardly from the duct inlet for suppressing dynamic pressure oscillations inside the conduit without degrading the pressure recovery.

Brush Seal

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US Patent:
53183096, Jun 7, 1994
Filed:
May 13, 1993
Appl. No.:
8/061330
Inventors:
Wu-Yang Tseng - West Chester OH
Christopher C. Glynn - Hamilton OH
Brent L. Bristol - Milford OH
Rolf R. Hetico - Cincinnati OH
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F16J 1532
US Classification:
277 53
Abstract:
An improved brush seal for reducing swirl, recirculation and turbulence of an approaching gas stream to reduce irregular bristle wear and operating costs. The brush real may include a baffle of the honeycomb type or circumferentially stacked plates type, positive or negative steps in the flow path approaching a seal stage, and recirculation breakers.

Thermally Responsive Labyrinth Seal

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US Patent:
45139750, Apr 30, 1985
Filed:
Apr 27, 1984
Appl. No.:
6/604561
Inventors:
Ambrose A. Hauser - Wyoming OH
Rolf R. Hetico - Cincinnati OH
Thomas G. Wakeman - Greendale IN
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F16J 1544
US Classification:
277 22
Abstract:
An improved rotary labyrinth seal such as may be used in a gas turbine engine. The seal includes a rotor with at least one seal tooth and a stator with an abradable shroud and casing. The first and second members cooperate to inhibit the flow of fluid therebetween. The improvement comprises a conduit for conducting a portion of the fluid through the casing for heat transfer between the fluid and second member. In this manner, the thermal response of the stator is improved.

Brush Seal

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US Patent:
55689310, Oct 29, 1996
Filed:
Aug 20, 1992
Appl. No.:
7/932463
Inventors:
Wu-Yang Tseng - West Chester OH
Brent L. Bristol - Milford OH
Rolf R. Hetico - Cincinnati OH
Christopher C. Glynn - Hamilton OH
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F16J 1548
US Classification:
277 53
Abstract:
There is provided by the present invention a brush seal including apparatus for reducing bristle vibrations, such as a damper, that engages the upstream side of the bristle pack of the brush seal so as to absorb vibrations and therefore reduce chamfering of the bristle pack.

Brush Seal

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US Patent:
53359208, Aug 9, 1994
Filed:
Aug 20, 1992
Appl. No.:
7/932514
Inventors:
Wu-Yang Tseng - West Chester OH
Brent L. Bristol - Milford OH
Rolf R. Hetico - Cincinnati OH
Christopher C. Glynn - Hamilton OH
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F16J 15447
US Classification:
277 1
Abstract:
A brush seal is provided having a plurality of bristle layers sandwiched between a pair of circumferential plates with the upstream layers of bristles having a higher first fundamental vibration frequency than downstream seal layers. Such a seal has bristles in the upstream layer or layers that have a greater cross sectional area, a lesser lay angle, are shorter, or some combination of the foregoing.
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Rolf R Hetico from Montgomery, OH, age ~67 Get Report