Patents by Inventor Hsin-tuan Liu
Hsin-tuan Liu 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).
-
Patent number: 7704038Abstract: A method for assembling a compressor for use with a turbine is provided. The method includes coupling at least a first stator ring to a second stator ring via at least one fastener sized to extend through at least one stator ring opening. The method further includes coupling a shield assembly to at least one of the first stator ring and the second stator ring to facilitate reducing convection and aerodynamic bleed losses of the at least one stator ring. The shield assembly includes a downstream surface, a retaining portion, and a contoured upstream surface extending from the downstream surface to the retaining portion.Type: GrantFiled: November 28, 2006Date of Patent: April 27, 2010Assignee: General Electric CompanyInventors: Matthew Joseph Ring, Samuel Rulli, Cory Kirk, Hsin-Tuan Liu, Apostolos Karafillis
-
Publication number: 20080120841Abstract: A method for assembling a compressor for use with a turbine is provided. The method includes coupling at least a first stator ring to a second stator ring via at least one fastener sized to extend through at least one stator ring opening. The method further includes coupling a shield assembly to at least one of the first stator ring and the second stator ring to facilitate reducing convection and aerodynamic bleed losses of the at least one stator ring. The shield assembly includes a downstream surface, a retaining portion, and a contoured upstream surface extending from the downstream surface to the retaining portion.Type: ApplicationFiled: November 28, 2006Publication date: May 29, 2008Inventors: Matthew Joseph Ring, Samuel Rulli, Cory Kirk, Hsin-Tuan Liu, Apostolos Karafillis
-
Patent number: 6905303Abstract: A method of assembling a gas turbine engine includes coupling an inner engine casing to an outer engine casing such that an annular flow path is defined therebetween, coupling a plurality of circumferentially-spaced support struts between the inner and outer casings, and coupling a plurality of circumferentially-spaced outlet guide vanes within the flow path upstream from the support struts, such that a first circumferential spacing is defined between a first guide vane and a second guide vane, and a second circumferential spacing is defined between the second guide vane and a third guide vane. The guide vanes are arranged such that the second guide vane is between the first and third guide vanes and the second circumferential spacing is different from the first circumferential spacing.Type: GrantFiled: June 30, 2003Date of Patent: June 14, 2005Assignee: General Electric CompanyInventors: Hsin-tuan Liu, William Andrew Bailey, John Doane Niedermeier
-
Publication number: 20040265124Abstract: A method of assembling a gas turbine engine includes coupling an inner engine casing to an outer engine casing such that an annular flow path is defined therebetween, coupling a plurality of circumferentially-spaced support struts between the inner and outer casings, and coupling a plurality of circumferentially-spaced outlet guide vanes within the flow path upstream from the support struts, such that a first circumferential spacing is defined between a first guide vane and a second guide vane, and a second circumferential spacing is defined between the second guide vane and a third guide vane. The guide vanes are arranged such that the second guide vane is between the first and third guide vanes and the second circumferential spacing is different from the first circumferential spacing.Type: ApplicationFiled: June 30, 2003Publication date: December 30, 2004Inventors: Hsin-Tuan Liu, William Andrew Bailey, John Doane Niedermeier
-
Patent number: 6508630Abstract: A compressor stator includes an outer casing supporting a row of stator vanes extending radially inwardly therefrom. Each vane includes pressure and suction sides extending axially between leading and trailing edges and radially between a root and a tip. The root and tip are twisted relative to a pitch section disposed therebetween. Each vane tip is radially convex adjacent a leading edge for defining an axially concave outer flowpath in the casing for reducing peak velocity of airflow for enhanced efficiency.Type: GrantFiled: March 30, 2001Date of Patent: January 21, 2003Assignee: General Electric CompanyInventors: Hsin-Tuan Liu, Brent Franklin Beacher, Bryan Keith Doloresco, Gregory Todd Steinmetz, Kenneth William Krabacher
-
Publication number: 20020150471Abstract: A variable inlet guide vane includes opposite pressure and suction sides extending along a chord between leading and trailing edges and in span from root to tip. The vane has a maximum thickness greater than about eight percent chord length and located less than about thirty-five percent chord length from the leading edge.Type: ApplicationFiled: March 30, 2001Publication date: October 17, 2002Inventors: Hsin-Tuan Liu, Brent Franklin Beacher, Robert Bruce Dickman
-
Publication number: 20020141863Abstract: A compressor stator includes an outer casing supporting a row of stator vanes extending radially inwardly therefrom. Each vane includes pressure and suction sides extending axially between leading and trailing edges and radially between a root and a tip. The root and tip are twisted relative to a pitch section disposed therebetween. Each vane tip is radially convex adjacent a leading edge for defining an axially concave outer flowpath in the casing for reducing peak velocity of airflow for enhanced efficiency.Type: ApplicationFiled: March 30, 2001Publication date: October 3, 2002Inventors: Hsin-Tuan Liu, Brent Franklin Beacher, Bryan Keith Doloresco, Gregory Todd Steinmetz, Kenneth William Krabacher
-
Patent number: 6457938Abstract: A variable inlet guide vane includes opposite pressure and suction sides extending along a chord between leading and trailing edges and in span from root to tip. The vane has a maximum thickness greater than about eight percent chord length and located less than about thirty-five percent chord length from the leading edge.Type: GrantFiled: March 30, 2001Date of Patent: October 1, 2002Assignee: General Electric CompanyInventors: Hsin-Tuan Liu, Brent Franklin Beacher, Robert Bruce Dickman
-
Patent number: 6331100Abstract: A compressor airfoil includes pressure and suction sides extending from root to tip and between leading and trailing edges. Transverse sections have respective chords and camber lines. Centers of gravity of the sections are aligned along a double bowed stacking axis for improving performance.Type: GrantFiled: December 6, 1999Date of Patent: December 18, 2001Assignee: General Electric CompanyInventors: Hsin-Tuan Liu, Robert B. Dickman, Kenneth W. Krabacher, Gregory T. Steinmetz, Brent F. Beacher, Bryan K. Doloresco
-
Patent number: 5279109Abstract: The present invention provides a gas turbine engine with a circumferentially disposed plurality of pivotal flow splitters between compressor sections to bleed off flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine engine, by pivoting the leading edge of the splitter into the compressor flow thereby using the total pressure Q of the flow to drive bleed flows overboard and remove particles.Type: GrantFiled: March 4, 1993Date of Patent: January 18, 1994Assignee: General Electric CompanyInventors: Hsin-Tuan Liu, William R. Hines
-
Patent number: 4344737Abstract: A crossover duct for providing flow communication between multiple stages of centrifugal compressors and the like. The duct forms a continuous annular path between compressor stages for turning radially outward gas flow to a radially inward direction. The duct includes thin diffuser vanes having aerodynamically contoured leading edges, and a vaneless turning bend having a generally elliptical wall geometry.Type: GrantFiled: January 30, 1978Date of Patent: August 17, 1982Assignee: The Garrett CorporationInventor: Hsin-Tuan Liu
-
Patent number: 4251183Abstract: A crossover duct assembly for providing flow communication between multiple stages of centrifugal compressors and the like. The duct assembly includes inner and outer wall sections forming a continuous annular flow path between compressor stages for turning radially outward gas flow to a radially inward direction. The duct includes a thin vane diffuser section, a vaneless turning bend having an elongated wall geometry, and a deswirl vane section for enhancing smooth gas flow with minimum pressure loss.Type: GrantFiled: January 30, 1978Date of Patent: February 17, 1981Assignee: The Garrett Corp.Inventors: Hsin-Tuan Liu, George L. Perrone, Leo E. Gambee