RICHARD DAVID CEDAR
Pilots at Buxton Ln, Cincinnati, OH
License number
Ohio A2517298
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
10341 Buxton Ln, Cincinnati, OH 45242
Professional information
Guide Vane And Method Of Fabricating The Same
US Patent:
2008015, Jul 3, 2008
Filed:
Dec 29, 2006
Appl. No.:
11/648508
Inventors:
Thomas Ory Moniz - Loveland OH, US
Robert Joseph Orlando - West Chester OH, US
Noel Istvan Macsotai - Loveland OH, US
Richard D. Cedar - Cincinnati OH, US
Robert Joseph Orlando - West Chester OH, US
Noel Istvan Macsotai - Loveland OH, US
Richard D. Cedar - Cincinnati OH, US
International Classification:
B21D 53/78, F01D 1/02, F01D 5/14
US Classification:
4151981, 2988971, 4152081
Abstract:
A method for fabricating an outlet guide vane includes the steps of fabricating a structural spar from a first material, fabricating a fairing from a second material, and installing the fairing onto the spar so as to at least partially surround the spar and form an airfoil. An outlet guide vane includes an airfoil including a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar. A gas turbine engine assembly includes a core gas turbine engine, a fan assembly including a plurality of fan blades coupled to the core gas turbine engine, and a plurality of outlet guide vanes coupled downstream from the fan blades, at least one of the outlet guide vanes including an airfoil having a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar.
Guide Vane And Method Of Fabricating The Same
US Patent:
2008015, Jul 3, 2008
Filed:
Mar 13, 2007
Appl. No.:
11/685299
Inventors:
Thomas Ory Moniz - Loveland OH, US
Robert Joseph Orlando - West Chester OH, US
Noel Istvan Macsotai - Loveland OH, US
Richard D. Cedar - Cincinnati OH, US
Robert Joseph Orlando - West Chester OH, US
Noel Istvan Macsotai - Loveland OH, US
Richard D. Cedar - Cincinnati OH, US
International Classification:
F03B 3/18
US Classification:
415159, 29888
Abstract:
A method for fabricating an outlet guide vane includes the steps of fabricating a structural spar from a first material, fabricating a fairing from a second material, and installing the fairing onto the spar so as to at least partially surround the spar and form an airfoil. An outlet guide vane includes an airfoil including a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar. A gas turbine engine assembly includes a core gas turbine engine, a fan assembly including a plurality of fan blades coupled to the core gas turbine engine, and a plurality of outlet guide vanes coupled downstream from the fan blades, at least one of the outlet guide vanes including an airfoil having a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar.
Row Of Long And Short Chord Length And High And Low Temperature Capability Turbine Airfoils
US Patent:
2004010, May 27, 2004
Filed:
Nov 27, 2002
Appl. No.:
10/305833
Inventors:
Mark Graham Turner - Cincinnati OH, US
Paul David Orkwis - Loveland OH, US
Richard David Cedar - Cincinnati OH, US
Paul David Orkwis - Loveland OH, US
Richard David Cedar - Cincinnati OH, US
International Classification:
F01D001/02
US Classification:
415/194000
Abstract:
A gas turbine engine turbine stage has an annular row of turbine airfoils including a first plurality of first airfoils having a first chord length and a second plurality of second airfoils having a second chord length shorter than the first chord length. At least one of the second airfoils is circumferentially disposed between each adjacent pair of the first airfoils. A second leading edges of the second airfoils are located downstream of first leading edges of the first airfoils. The first and second airfoils have different first and second temperature capabilities respectively and the first temperature capability is greater than the second temperature capability. The first and second airfoils may be made from different alloys and/or the second airfoils may be constructed to use lower amounts of cooling airflow than the first airfoils. More than one of the second airfoils may be disposed between each pair of the first airfoils.
System And Method For Reduction Of Unsteady Pressures In Turbomachinery
US Patent:
2009031, Dec 24, 2009
Filed:
Jun 20, 2008
Appl. No.:
12/142940
Inventors:
Trevor Howard Wood - Clifton Park NY, US
Kishore Ramakrishnan - Clifton Park NY, US
Richard David Cedar - Cincinnati OH, US
Kishore Ramakrishnan - Clifton Park NY, US
Richard David Cedar - Cincinnati OH, US
Assignee:
GENERAL ELECTRIC COMPANY - SCHENECTADY NY
International Classification:
F04D 29/66
US Classification:
415119, 4151213, 2988921
Abstract:
A turbomachinery system is provided. The system includes a first set of blades and a second set of blades moving relative to the first set of blades, wherein the second set of blades includes a first subset of blades having multiple first geometric parameters. The second set of blades also includes at least a second subset of blades non-uniformly spaced circumferentially and axially relative to the first subset of blades such that unsteady pressures generated from the wakes of the first set of blades interacting with the second set of blades is below an acceptable level. Further, the at least second subset of blades include multiple second geometric parameters that are different or identical to the multiple first geometric parameters.
Variable Slope Exhaust Nozzle
US Patent:
2010005, Mar 4, 2010
Filed:
Aug 27, 2008
Appl. No.:
12/198959
Inventors:
Mustafa Dindar - Cincinnati OH, US
Scott Andrew Burton - Cincinnati OH, US
Keith Edward James Blodgett - Milford OH, US
Richard David Cedar - Cincinnati OH, US
Scott Andrew Burton - Cincinnati OH, US
Keith Edward James Blodgett - Milford OH, US
Richard David Cedar - Cincinnati OH, US
International Classification:
F02K 1/00
US Classification:
60770
Abstract:
A turbine exhaust nozzle includes an inner shell disposed coaxially inside an outer shell to define a flow duct terminating in an outlet at a trailing edge of the outer shell. The inner shell is non-axisymmetric and varies in axial slope angle circumferentially around the duct.