Patents by Inventor Stephen D. Doll
Stephen D. Doll has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11795826Abstract: A turbine blade for use in a gas turbine engine includes localized thickening of a neck pocket of the turbine blade to meet strength requirements while minimizing the weight of the turbine blade. More specifically, a convex spline is positioned within a suction side neck pocket of the turbine blade adjacent a leading edge of the neck pocket to increase the strength of the blade.Type: GrantFiled: February 15, 2022Date of Patent: October 24, 2023Assignee: RTX CORPORATIONInventors: Carlos Calixtro, Stephen D. Doll
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Publication number: 20230258089Abstract: A turbine blade for use in a gas turbine engine includes localized thickening of a neck pocket of the turbine blade to meet strength requirements while minimizing the weight of the turbine blade. More specifically, a convex spline is positioned within a suction side neck pocket of the turbine blade adjacent a leading edge of the neck pocket to increase the strength of the blade.Type: ApplicationFiled: February 15, 2022Publication date: August 17, 2023Inventors: Carlos Calixtro, Stephen D. Doll
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Patent number: 11143040Abstract: A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y? and Z? axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y? and Z? axis datum with respect to the Y? and Z? axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum; and machining off the sacrificial datum system removing the V-notches.Type: GrantFiled: October 2, 2019Date of Patent: October 12, 2021Assignee: Raytheon Technologies CorporationInventors: Michael G. McCaffrey, Karl A. Mentz, Christopher King, Stephen D. Doll, Aurelia Ledbetter
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Publication number: 20210102468Abstract: A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y? and Z? axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y? and Z? axis datum with respect to the Y? and Z? axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y? and Z? axis datum; and machining off the sacrificial datum system removing the V-notches.Type: ApplicationFiled: October 2, 2019Publication date: April 8, 2021Applicant: United Technologies CorporationInventors: Michael G. McCaffrey, Karl A. Mentz, Christopher King, Stephen D. Doll, Aurelia Ledbetter
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Patent number: 9024226Abstract: A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.Type: GrantFiled: July 9, 2012Date of Patent: May 5, 2015Assignee: United Technologies CorporationInventors: Glenn Levasseur, Edward F. Pietraszkiewicz, Mark F. Zelesky, Dominic J. Mongillo, Jr., Kevin J. Klinefelter, Stephen D. Doll, Markus W. Fritch
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Publication number: 20130206733Abstract: A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.Type: ApplicationFiled: July 9, 2012Publication date: August 15, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Glenn Levasseur, Edward F. Pietraszkiewicz, Mark F. Zelesky, Dominic J. Mongillo, JR., Kevin J. Klinefelter, Stephen D. Doll, Markus W. Fritch
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Patent number: 8011892Abstract: A turbine blade damper-seal assembly includes a seal nested within a damper such that both the seal and damper are disposed to provide sealing between adjacent blade platforms. The seal traverses the seal slot in the damper and seals the gap between adjacent blade platforms for the full axial length of the neck cavity between adjacent blades. The damper is located in an aft most position and includes features to facilitate vibration-dampening performance. The damper also includes features that cause entrapment between blades and therefore avoids the conventionally required protrusions on the blade to retain it in the assembled position.Type: GrantFiled: June 28, 2007Date of Patent: September 6, 2011Assignee: United Technologies CorporationInventors: Amarnath Ramlogan, Rajendra K. Agrawal, Stephen D. Doll
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Patent number: 7578178Abstract: A method of inspecting an internal feature of a gas turbine component includes removing a portion of the turbine component to expose the internal feature, treating the surfaces of the internal feature to provide the surfaces with a substantially uniform coloration, generating an electronic model of the internal feature, analyzing the electronic model generated with reference to a nominal electronic model, and providing an output based on the analysis of the electronic model generated.Type: GrantFiled: September 28, 2007Date of Patent: August 25, 2009Assignee: United Technologies CorporationInventors: Jesse R. Boyer, Benjamin W. Meissner, Stephen D. Doll, Randall W. Joyner
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Publication number: 20090089020Abstract: A method of inspecting an internal feature of a gas turbine component includes removing a portion of the turbine component to expose the internal feature, treating the surfaces of the internal feature to provide the surfaces with a substantially uniform coloration, generating an electronic model of the internal feature, analyzing the electronic model generated with reference to a nominal electronic model, and providing an output based on the analysis of the electronic model generated.Type: ApplicationFiled: September 28, 2007Publication date: April 2, 2009Applicant: United Technologies CorporationInventors: Jesse R. Boyer, Benjamin W. Meissner, Stephen D. Doll, Randall W. Joyner
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Publication number: 20090004013Abstract: A turbine blade damper-seal assembly includes a seal nested within a damper such that both the seal and damper are disposed to provide sealing between adjacent blade platforms. The seal traverses the seal slot in the damper and seals the gap between adjacent blade platforms for the full axial length of the neck cavity between adjacent blades. The damper is located in an aft most position and includes features to facilitate vibration-dampening performance. The damper also includes features that cause entrapment between blades and therefore avoids the conventionally required protrusions on the blade to retain it in the assembled position.Type: ApplicationFiled: June 28, 2007Publication date: January 1, 2009Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Amarnath Ramlogan, Rajendra K. Agrawal, Stephen D. Doll
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Publication number: 20080003096Abstract: A cooling hole for a gas turbine engine component has a bi-lobed shape to improve cooling effectiveness. The gas turbine engine component has a first outer surface and a second outer surface separated from each other by a thickness. The cooling hole extends through the thickness from a first opening at the first outer surface to a second opening at the second outer surface. The first and second openings are defined by shapes that are different from each other. One of the first and second openings has the bi-lobed shape.Type: ApplicationFiled: June 29, 2006Publication date: January 3, 2008Inventors: Atul Kohli, Joseph B. Staubach, Stephen D. Doll