Patents by Inventor Scott L. Stafford
Scott L. Stafford 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: 11428166Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.Type: GrantFiled: November 12, 2020Date of Patent: August 30, 2022Assignee: Solar Turbines IncorporatedInventors: Scott L. Stafford, Juan Yin, Steven D. Gray
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Publication number: 20220145799Abstract: Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.Type: ApplicationFiled: November 12, 2020Publication date: May 12, 2022Applicant: Solar Turbines IncorporatedInventors: Scott L. Stafford, Juan Yin, Steven D. Gray
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Patent number: 10927691Abstract: This disclosure provides a seal strip assembly for a sealing strip slot to reduce air leakage between gas turbine nozzle segments. The seal strip assembly includes a bimetal element and a backing plate. The bimetal element includes a first layer with a first thermal coefficient of thermal expansion and a second layer with a second coefficient of thermal expansion. The second coefficient of thermal expansion is lower than the first coefficient of thermal expansion allowing the bimetal element to expand with an increase in surrounding temperature.Type: GrantFiled: March 21, 2019Date of Patent: February 23, 2021Assignee: Solar Turbines IncorporatedInventors: Scott L. Stafford, Michael Theodore Austin, Matthew Novaresi, James Maleski, John Francis Lorentzen, Manuel Iribe-Moreno, Garrett Prins, Keith Levon Harrell
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Publication number: 20200300110Abstract: This disclosure provides a seal strip assembly for a sealing strip slot to reduce air leakage between gas turbine nozzle segments. The seal strip assembly includes a bimetal element and a backing plate. The bimetal element includes a first layer with a first thermal coefficient of thermal expansion and a second layer with a second coefficient of thermal expansion. The second coefficient of thermal expansion is lower than the first coefficient of thermal expansion allowing the bimetal element to expand with an increase in surrounding temperature.Type: ApplicationFiled: March 21, 2019Publication date: September 24, 2020Applicant: Solar Turbines IncorporatedInventors: Scott L. Stafford, Michael Theodore Austin, Matthew Novaresi, James Maleski, John Francis Lorentzen, Manuel Iribe-Moreno, Garrett Prins, Keith Levon Harrell
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Patent number: 10233782Abstract: A turbine assembly of an engine is disclosed. The turbine assembly includes a nozzle ring for receiving exhaust gases from a combustion chamber having a plurality of guide vanes for guiding the exhaust gases, a stator ring disposed downstream to the nozzle ring, and a rotor disposed circumferentially within the stator ring. The stator ring includes a plurality of stator vanes adapted to receive the exhaust gases through the guide vanes of the nozzle ring. The stator ring is axially movable between a first position and a second position along at least one cross-key pin disposed between the stator ring and a turbine casing. Each of the plurality of stator vanes moves into a throat plane of each pair of the plurality of guide vanes in the first position of the stator ring, and moves out of the throat plane in the second position of the stator ring.Type: GrantFiled: August 3, 2016Date of Patent: March 19, 2019Assignee: Solar Turbines IncorporatedInventor: Scott L. Stafford
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Patent number: 9938841Abstract: A preswirler for a gas turbine engine diaphragm assembly is disclosed herein. In embodiments, the preswirler includes an outer ring and an inner ring. The outer ring includes an outer ring face, a first contact protrusion, and a second contact protrusion. The first and second contact protrusions are spaced apart and extend from an outer body portion at the outer ring face. The inner ring is located inward from the outer ring. The inner ring includes an inner ring face and a third contact protrusion. The third contact protrusion extends in from an inner body portion and at the inner ring face.Type: GrantFiled: August 18, 2015Date of Patent: April 10, 2018Assignee: Solar Turbines IncorporatedInventor: Scott L. Stafford
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Patent number: 9890660Abstract: A spacer for a diaphragm assembly coupling is disclosed. The spacer includes a base, a spacing portion, and a spacing body edge. The base includes a base body including a base edge. The spacing portion includes a spacing body and a spacing flange. The spacing body extends from the base and includes an outer diameter that is smaller than that of the base. The spacing flange extends outward from the spacing body and is spaced apart from the base. The spacing body edge is located at an intersection of the spacing body and the base body. A reference line extending from the spacing body edge to the base edge forms an angle from 10 to 30 degrees with the spacer axis.Type: GrantFiled: September 18, 2014Date of Patent: February 13, 2018Assignee: Solar Turbines IncorporatedInventor: Scott L. Stafford
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Publication number: 20180038239Abstract: A turbine assembly of an engine is disclosed. The turbine assembly includes a nozzle ring for receiving exhaust gases from a combustion chamber having a plurality of guide vanes for guiding the exhaust gases, a stator ring disposed downstream to the nozzle ring, and a rotor disposed circumferentially within the stator ring. The stator ring includes a plurality of stator vanes adapted to receive the exhaust gases through the guide vanes of the nozzle ring. The stator ring is axially movable between a first position and a second position along at least one cross-key pin disposed between the stator ring and a turbine casing. Each of the plurality of stator vanes moves into a throat plane of each pair of the plurality of guide vanes in the first position of the stator ring, and moves out of the throat plane in the second position of the stator ring.Type: ApplicationFiled: August 3, 2016Publication date: February 8, 2018Applicant: Solar Turbines IncorporatedInventor: Scott L. Stafford
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Publication number: 20160084112Abstract: A spacer for a diaphragm assembly coupling is disclosed. The spacer includes a base, a spacing portion, and a spacing body edge. The base includes a base body including a base edge. The spacing portion includes a spacing body and a spacing flange. The spacing body extends from the base and includes an outer diameter that is smaller than that of the base. The spacing flange extends outward from the spacing body and is spaced apart from the base. The spacing body edge is located at an intersection of the spacing body and the base body. A reference line extending from the spacing body edge to the base edge forms an angle from 10 to 30 degrees with the spacer axis.Type: ApplicationFiled: September 18, 2014Publication date: March 24, 2016Applicant: SOLAR TURBINES INCORPORATEDInventor: Scott L. Stafford
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Publication number: 20160084095Abstract: A preswirler for a gas turbine engine diaphragm assembly is disclosed herein. In embodiments, the preswirler includes an outer ring and an inner ring. The outer ring includes an outer ring face, a first contact protrusion, and a second contact protrusion. The first and second contact protrusions are spaced apart and extend from an outer body portion at the outer ring face. The inner ring is located inward from the outer ring. The inner ring includes an inner ring face and a third contact protrusion. The third contact protrusion extends in from an inner body portion and at the inner ring face.Type: ApplicationFiled: August 18, 2015Publication date: March 24, 2016Applicant: SOLAR TURBINES INCORPORATEDInventor: Scott L. Stafford
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Patent number: 9175566Abstract: A gas turbine engine preswirler (470) includes an outer ring (471) and an inner ring (472). The inner ring (472) includes a plurality of angled holes (490). Each angled hole (490) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular a radial from an axis of the preswirler (470). The component of the angle is angled relative to an axial direction of the preswirler (470).Type: GrantFiled: September 26, 2012Date of Patent: November 3, 2015Assignee: Solar Turbines IncorporatedInventors: Hongzhou Xu, Michael D. Fox, Scott L. Stafford, Edward T. Ramirez
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Patent number: 9151696Abstract: A gage tool (700) for inspecting tolerances of a gas turbine engine seal plate (430) includes a base plate (710) and a top plate (720). The base plate (710) includes a base opening (712) and a slot (711) with an annular shape sized to receive a seal plate (430). The top plate (720) includes a top opening (723). The base opening (712) and top opening (723) each provide access to a portion of a seal plate (430) within the gage tool (700). The gage tool (700) also includes a first gage (750) with a probe tip for measuring a variation in an outer interlacing surface (433) of a seal plate (430) and a seal slide gage (740) for measuring a force required to rotate the seal plate (430) within the gage tool.Type: GrantFiled: December 12, 2012Date of Patent: October 6, 2015Assignee: Solar Turbines IncorporatedInventors: James Brian Powell, Scott L. Stafford, Luvern John Weber, Terry Toshio Akiyama
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Publication number: 20140157596Abstract: A gage tool (700) for inspecting tolerances of a gas turbine engine seal plate (430) includes a base plate (710) arid a top plate (720). The base plate (710) includes abase opening (712) and a slot (711) with an annular shape sized to receive a seal plate (430). The top plate (720) Includes a top opening (723). The base opening (712) and top opening (723) each provide access to a portion of a seal plate (430) within the gage tool (700). The gage tool (700) also includes a first gage (750) with a probe tip for measuring a variation in an outer interlacing surface (433) of a seal plate (430) and a seal slide gage (740) for measuring a force required to rotate Ore seal plate (430) within the gage tool.Type: ApplicationFiled: December 12, 2012Publication date: June 12, 2014Applicant: SOLAR TURBINES INCORPORATEDInventors: James Brian Powell, Scott L. Stafford, Luvern John Weber, Terry Toshio Akiyama
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Publication number: 20140083101Abstract: A gas turbine engine preswirler (470) includes an outer ring (471) and an inner ring (472). The inner ring (472) includes a plurality of angled holes (490). Each angled hole (490) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular a radial from an axis of the preswirler (470). The component of the angle is angled relative to an axial direction of the preswirler (470).Type: ApplicationFiled: September 26, 2012Publication date: March 27, 2014Applicant: SOLAR TURBINES INCORPORATEDInventors: Hongzhou Xu, Michael D. Fox, Scott L. Stafford, Edward T. Ramirez
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Patent number: 4411837Abstract: Unsymmetrical carbonates of the formula ##STR1## are prepared by the following reaction sequence ##STR2## where R and R' can each be --CH.sub.2 C(NO.sub.2).sub.3, CH.sub.2 CF(NO..2).sub.2, --CH.sub.2 CF.sub.2 (NO.sub.2), --CH.sub.2 CCl(NO.sub.2).sub.2, --CH.sub.2 CF.sub.3, --CH.sub.2 CCl.sub.3, --CH.sub.2 C(NO.sub.2).sub.2 CH.sub.3, or --CH.sub.2 CF.sub.2 CF.sub.2 H, provided that R.noteq.R' and wherein R" is a lower alkyl group of from 1 to 6 carbon atoms.Also included are symmetrical 1,3-bis(halo- and nitroalkyl carbonyldioxy)-2,2-dinitropropanes of the formula ##STR3## which are synthesis by the following reaction sequence ##STR4## wherein R and R" are as defined above. The carbonates of this invention are useful as energetic additives to propellants and explosive.Type: GrantFiled: March 3, 1982Date of Patent: October 25, 1983Assignee: The United States of America as represented by the Secretary of the NavyInventors: William H. Gilligan, Scott L. Stafford
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Patent number: 4411838Abstract: Unsymmetrical carbonates of the formula ##STR1## are prepared by the following reaction sequence ##STR2## where R and R' can each be --CH.sub.2 C(NO.sub.2).sub.3, CH.sub.2 CF(NO..2).sub.2, --CH.sub.2 CF.sub.2 (NO.sub.2), --CH.sub.2 CCl(NO.sub.2).sub.2, --CH.sub.2 CF.sub.3, --CH.sub.2 CCl.sub.3, --CH.sub.2 C(NO.sub.2).sub.2 CH.sub.3, or --CH.sub.2 CF.sub.2 CF.sub.2 H, provided that R.noteq.R' and wherein R" is a lower alkyl group of from 1 to 6 carbon atoms.Also included are symmetrical 1,3-bis(halo- and nitroalkyl carbonyldioxy)-2,2-dinitropropanes of the formula ##STR3## which are synthesis by the following reaction sequence ##STR4## wherein R and R" are as defined above. The carbonates of this invention are useful as energetic additives to propellants and explosive.Type: GrantFiled: March 3, 1982Date of Patent: October 25, 1983Assignee: The United States of America as represented by the Secretary of the NavyInventors: William H. Gilligan, Scott L. Stafford
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Patent number: 4332744Abstract: Unsymmetrical carbonates of the formula ##STR1## are prepared by the following reaction sequence ##STR2## where R and R' can each be --CH.sub.2 C(NO.sub.2).sub.3, CH.sub.2 CF(NO..2).sub.2, --CH.sub.2 CF.sub.2 (NO.sub.2), --CH.sub.2 CCl(NO.sub.2).sub.2, --CH.sub.2 CF.sub.3, --CH.sub.2 CCl.sub.3, --CH.sub.2 C(NO.sub.2).sub.2 CH.sub.3, or --CH.sub.2 CF.sub.2 CF.sub.2 H, provided that R.noteq.R' and wherein R" is a lower alkyl group of from 1 to 6 carbon atoms.Also included are symmetrical 1,3-bis(halo- and nitroalkyl carbonyldioxy)-2,2-dinitropropanes of the formula ##STR3## which are synthesis by the following reaction sequence ##STR4## wherein R and R" are as defined above. The carbonates of this invention are useful as energetic additives to propellants and explosive.Type: GrantFiled: January 13, 1981Date of Patent: June 1, 1982Assignee: The United States of America as represented by the Secretary of the NavyInventors: William H. Gilligan, Scott L. Stafford