Patents by Inventor Jae Y. Um
Jae Y. Um 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: 11415000Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.Type: GrantFiled: June 4, 2018Date of Patent: August 16, 2022Assignee: Siemens Energy Global GmbH & Co. KGInventors: Ching-Pang Lee, Jae Y. Um, Sin Chien Siw, Anthony Waywood, Harry Holloman, Steven Koester
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Turbine rotor airfoil and corresponding method for reducing pressure loss in a cavity within a blade
Patent number: 11111795Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.Type: GrantFiled: August 7, 2018Date of Patent: September 7, 2021Assignee: Siemens Energy Global GmbH & Co. KGInventors: Ching-Pang Lee, Harry Holloman, Steven Koester, Jae Y. Um, Sin Chien Siw -
Publication number: 20210140321Abstract: A turbine airfoil includes a trailing edge coolant cavity between a pressure sidewall and a suction sidewall. The trailing edge coolant cavity is positioned adjacent to and extending out to a trailing edge of the turbine airfoil. The interior includes an internal arrangement comprising an array of discrete fins formed aft of the trailing edge coolant cavity along the trailing edge.Type: ApplicationFiled: June 4, 2018Publication date: May 13, 2021Inventors: Ching-Pang Lee, Jae Y. Um, Sin Chien Siw, Anthony Waywood, Harry Holloman, Steven Koester
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TURBINE ROTOR AIRFOIL AND CORRESPONDING METHOD FOR REDUCING PRESSURE LOSS IN A CAVITY WITHIN A BLADE
Publication number: 20210025278Abstract: A blade airfoil for a turbine engine that includes an internal multiple pass serpentine flow cooling circuits with a leading edge circuit and a trailing edge circuit. The entrance of a cavity in the leading edge circuit has a narrowing of a cavity width that expands further downstream to a consistent cavity width similar to the cavity width of the rest of the leading edge circuit.Type: ApplicationFiled: August 7, 2018Publication date: January 28, 2021Inventors: Ching-Pang Lee, Harry Holloman, Steven Koester, Jae Y. Um, Sin Chien Siw -
Patent number: 10697306Abstract: A core structure (10) includes a first core element (16) including a leading edge section (30), a tip section (32), and a turn section (34) joining the leading edge and tip sections (30, 32). The first core element (16) is adapted to be used to form a leading edge cooling circuit (102) in a gas turbine engine airfoil (100). The leading edge cooling circuit (102) includes a cooling fluid passage (104) having a leading edge portion (106) formed by the first core element leading edge section (30), a tip portion (108) formed by the first core element tip section (32), and a turn portion (110) formed by the first core element turn section (34). Each of the leading edge portion (106), the tip portion (108), and the turn portion (110) of the cooling fluid passage (104) are formed concurrently in the airfoil (100) by the first core element (16).Type: GrantFiled: September 18, 2014Date of Patent: June 30, 2020Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Ching-Pang Lee, Jae Y. Um, Gerald L. Hillier, Wayne J. McDonald, Erik Johnson, Anthony Waywood, Eric Schroeder, Zhengxiang Pu
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Publication number: 20180298763Abstract: The present disclosure provides a turbine blade (12) comprising a leading edge cooling circuit (30), a trailing edge cooling circuit (34), a mid-section cooling circuit (32) comprising a first channel (32a), an intermediate channel (32b), and a final channel (32c), and an axial tip cooling circuit (56). The leading edge, mid-section, and trailing edge cooling circuits (30, 32, 34) each receive a cooling airflow (CF) from a cooling air supply. A radially outer portion of each of the leading edge and mid-section cooling circuits (30, 32) further comprises at least one outlet (62, 64) in fluid communication with the axial tip cooling circuit (56) such that substantially all of a leading edge cooling airflow (LEF) exiting the leading edge cooling circuit (30) and substantially all of a mid-section cooling airflow (MSF) exiting the mid-section cooling circuit (32) is directed to the axial tip cooling circuit (56).Type: ApplicationFiled: November 11, 2014Publication date: October 18, 2018Inventors: Ching-Pang Lee, Jae Y. Um, Gerald L. Hillier, Eric Schroeder, Erik Johnson, Dustin Muller
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Patent number: 9963996Abstract: A shroud cooling system configured to cool a shroud adjacent to an airfoil within a gas turbine engine is disclosed. The turbine engine shroud may be formed from shroud segments that include a plurality of cooling air supply channels extending through a forward shroud support for impingement of cooling air onto an outer radial surface of the shroud segment with respect to the inner turbine section of the turbine engine. The channels may extend at various angles to increase cooling efficiency. The backside surface may also include various cooling enhancement components configured to assist in directing, dispersing, concentrating, or distributing cooling air impinged thereon from the channels to provide enhanced cooling at the backside surface. The shroud cooling system may be used to slow down the thermal response by isolating a turbine vane carrier from the cooling fluids while still providing efficient cooling to the shroud.Type: GrantFiled: August 22, 2014Date of Patent: May 8, 2018Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Darryl Eng, Christopher Rawlings, Thomas Pechette, Friedrich T. Rogers, Jae Y. Um, Ching-Pang Lee
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Publication number: 20180045059Abstract: An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (12) forming the generally hollow elongated airfoil (26). In addition, heat may be extracted in the midchord region (150) via one or more heat dissipating ribs (152) extending partially between an inner surface (144) of the suction side (38) and the insert (18).Type: ApplicationFiled: April 17, 2015Publication date: February 15, 2018Inventors: Ching-Pang Lee, Jae Y. Um, Zhengxiang Pu, Caleb Myers
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Patent number: 9863256Abstract: An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows. In at least one embodiment, the cooling fluid flow controllers (22) may be positioned within a pressure side nearwall cooling channel (48) and a suction side nearwall cooling channel (50) that are both in fluid communication with a trailing edge channel (30). The trailing edge channel (30) may also include cooling fluid flow controllers (22) extending between the outer walls (12, 13) forming the pressure and suction sides.Type: GrantFiled: September 4, 2014Date of Patent: January 9, 2018Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Ching-Pang Lee, Jae Y. Um, Zhengxiang Pu, Mohamed Abdullah, Eric Schroeder, Anthony Waywood
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Patent number: 9840930Abstract: An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained therein that forms nearwall cooling channels (20) having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows (28), and the internal cooling system (14) may include one or more bypass flow reducers (30) extending from the insert (18) toward the outer wall (24) to direct the cooling fluids through the channels (20) created by the cooling fluid flow controllers (22), thereby increasing the effectiveness of the internal cooling system (14).Type: GrantFiled: September 4, 2014Date of Patent: December 12, 2017Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Ching-Pang Lee, Jae Y. Um, Gerald L. Hillier, Wayne J. McDonald, Mohamed Abdullah, Eric Schroeder, Ralph W. Matthews, Zhengxiang Pu
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Publication number: 20170275998Abstract: A core structure (10) includes a first core element (16) including a leading edge section (30), a tip section (32), and a turn section (34) joining the leading edge and tip sections (30, 32). The first core element (16) is adapted to be used to form a leading edge cooling circuit (102) in a gas turbine engine airfoil (100). The leading edge cooling circuit (102) includes a cooling fluid passage (104) having a leading edge portion (106) formed by the first core element leading edge section (30), a tip portion (108) formed by the first core element tip section (32), and a turn portion (110) formed by the first core element turn section (34). Each of the leading edge portion (106), the tip portion (108), and the turn portion (110) of the cooling fluid passage (104) are formed concurrently in the airfoil (100) by the first core element (16).Type: ApplicationFiled: September 18, 2014Publication date: September 28, 2017Applicant: Siemens AktiengesellschaftInventors: Ching-Pang Lee, Jae Y. Um, Gerald L. Hillier, Wayne J. McDonald, Erik Johnson, Anthony Waywood, Eric Schroeder, Zhengxiang Pu
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Publication number: 20170268358Abstract: An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities (16) having an insert (18) contained therein that forms nearwall cooling channels (20) having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels (20) may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows (28), and the internal cooling system (14) may include one or more bypass flow reducers (30) extending from the insert (18) toward the outer wall (24) to direct the cooling fluids through the channels (20) created by the cooling fluid flow controllers (22), thereby increasing the effectiveness of the internal cooling system (14).Type: ApplicationFiled: September 4, 2014Publication date: September 21, 2017Inventors: Ching-Pang Lee, Jae Y. Um, Gerald L. Hillier, Wayne J. McDonald, Mohamed Abdullah, Eric Schroeder, Ralph W. Matthews, Zhengxiang Pu
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Publication number: 20170268348Abstract: An airfoil (10) for a gas turbine engine in which the airfoil (10) includes an internal cooling system (14) with one or more internal cavities having an insert (18) contained within an aft cooling cavity (76) to form nearwall cooling channels having enhanced flow patterns is disclosed. The flow of cooling fluids in the nearwall cooling channels may be controlled via a plurality of cooling fluid flow controllers (22) extending from the outer wall (24) forming the generally hollow elongated airfoil (26). The cooling fluid flow controllers (22) may be collected into spanwise extending rows. In at least one embodiment, the cooling fluid flow controllers (22) may be positioned within a pressure side nearwall cooling channel (48) and a suction side nearwall cooling channel (50) that are both in fluid communication with a trailing edge channel (30). The trailing edge channel (30) may also include cooling fluid flow controllers (22) extending between the outer walls (12, 13) forming the pressure and suction sides.Type: ApplicationFiled: September 4, 2014Publication date: September 21, 2017Inventors: Ching-Pang Lee, Jae Y. Um, Zhengxiang Pu, Mohamed Abdullah, Eric Schroeder, Anthony Waywood
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Patent number: 9745853Abstract: A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.Type: GrantFiled: August 31, 2015Date of Patent: August 29, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Ching-Pang Lee, Nan Jiang, Jae Y. Um, Harry Holloman, Steven Koester
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Publication number: 20170183978Abstract: A shroud cooling system (100) configured to cool a shroud (50) adjacent to an airfoil within a gas turbine engine (10) is disclosed. The turbine engine shroud (50) may be formed from shroud segments (34) that include a plurality of cooling air supply channels (40) extending through a forward shroud support (52) for impingement of cooling air onto an outer radial surface of the shroud segment (34) with respect to the inner turbine section of the turbine engine (10). The channels (40) may extend at various angles (42) to increase cooling efficiency. The backside surface (62) may also include various cooling enhancement components configured to assist in directing, dispersing, concentrating, or distributing cooling air impinged thereon from the channels (40) to provide enhanced cooling at the backside surface (62).Type: ApplicationFiled: August 22, 2014Publication date: June 29, 2017Inventors: Darryl Eng, Christopher Rawlings, Thomas Pechette, Friedrich T. Rogers, Jae Y. Um, Ching-Pang Lee
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Patent number: 9630277Abstract: A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.Type: GrantFiled: March 15, 2010Date of Patent: April 25, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Ching-Pang Lee, Mrinal Munshi, Gm S. Azad, Jae Y. Um
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Publication number: 20170058678Abstract: A turbine rotor blade includes at least two integrated cooling circuits that are formed within the blade that include a leading edge circuit having a first cavity and a second cavity and a trailing edge circuit that includes at least a third cavity located aft of the second cavity. The trailing edge circuit flows aft with at least two substantially 180-degree turns at the tip end and the root end of the blade providing at least a penultimate cavity and a last cavity. The last cavity is located along a trailing edge of the blade. A tip axial cooling channel connects to the first cavity of the leading edge circuit and the penultimate cavity of the trailing edge circuit. At least one crossover hole connects the penultimate cavity to the last cavity substantially near the tip end of the blade.Type: ApplicationFiled: August 31, 2015Publication date: March 2, 2017Inventors: Ching-Pang Lee, Nan Jiang, Jae Y. Um, Harry Holloman, Steven Koester
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Patent number: 9181819Abstract: A film cooling structure formed in a component wall of a turbine engine and a method of making the film cooling structure. The film cooling structure includes a plurality of individual diffusion sections formed in the wall, each diffusions section including a single cooling passage for directing cooling air toward a protuberance of a wall defining the diffusion section. The film cooling structure may be formed with a masking template including apertures defining shapes of a plurality of to-be-formed diffusion sections in the wall. A masking material can be applied to the wall into the apertures in the masking template so as to block outlets of cooling passages exposed through the apertures. The masking template can be removed and a material may be applied on the outer surface of the wall such that the material defines the diffusion sections once the masking material is removed.Type: GrantFiled: June 11, 2010Date of Patent: November 10, 2015Assignee: Siemens Energy, Inc.Inventors: Ching-Pang Lee, Jae Y. Um, Mrinal Munshi, Humberto A. Zuniga
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Publication number: 20150239043Abstract: A method for casting an object (12) having an integrated surface feature (10) for location, inspection, and analysis using a feature-based vision system is provided herein that includes determining a shape geometry for a surface feature (10), wherein the shape geometry is adapted for tracking with a feature-based vision system, determining a proper size, placement, and orientation for the surface feature (10) based on a type of inspection, and casting the surface feature (10) into an object (12) at the determined placement and orientation using an investment casting process to produce an integrated surface feature.Type: ApplicationFiled: February 21, 2014Publication date: August 27, 2015Applicant: Siemens Energy, Inc.Inventors: Jonathan E. Shipper, JR., Samuel R. Miller, JR., Jae Y. Um, Michael E. Crawford, Gary B. Merrill, Ahmed Kamel
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Publication number: 20150204197Abstract: An airfoil cooling arrangement (12), including: a leading edge chamber (54) configured to cool an interior surface (68) of an airfoil; and an impingement orifice (60) configured to direct an impingement jet (64) toward an impingement location (66) disposed on the interior surface and offset from a camber line (28) of the airfoil The airfoil cooling arrangement is effective to guide post impingement cooling fluid along the interior surface, through a leading portion (76) of the leading edge chamber, and then back toward a trailing edge (22) of the airfoil in a helical motion (114).Type: ApplicationFiled: January 23, 2014Publication date: July 23, 2015Inventors: Ching-Pang Lee, Jae Y. Um, Gerald L. Hillier, Eric Schroeder, Erik Johnson