Patents by Inventor Yun Chang Jang
Yun Chang Jang 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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Publication number: 20240075620Abstract: A functional safety system of a robot according to an exemplary embodiment of the present disclosure can generate a safety zone which is a zone to sense whether an obstacle is present.Type: ApplicationFiled: May 12, 2023Publication date: March 7, 2024Inventors: Seong Ju PARK, Dong Hyeon SEO, Seung Ho JANG, Min Chang, Yun Jib Kim, Chang Woo Kim
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Publication number: 20240077618Abstract: A functional safety system of a robot according to an exemplary embodiment of the present disclosure can duplicate modules so as to satisfy a performance level d (pl-d) required for the functional satisfy of a robot.Type: ApplicationFiled: May 12, 2023Publication date: March 7, 2024Inventors: Seong Ju PARK, Dong Hyeon SEO, Seung Ho JANG, Min Chang, Yun Jib Kim, Chang Woo Kim
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Publication number: 20240075622Abstract: A functional safety system of a robot according to an exemplary embodiment of the present disclosure can duplicate modules so as to satisfy a performance level d (pl-d) required for the functional satisfy of a robot.Type: ApplicationFiled: May 12, 2023Publication date: March 7, 2024Inventors: Seong Ju PARK, Dong Hyeon SEO, Seung Ho JANG, Min Chang, Yun Jib Kim, Chang Woo Kim
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Publication number: 20230366327Abstract: A ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade existing inside the casing, the ring segment includes a segment body disposed inside the casing in a radial direction of the casing and having a channel through which cooling air flows, and a pair of segment protrusions protruding outward from the segment body, coupled to the inner circumferential surface of the casing, and spaced apart from each other along a flow direction of fluid flowing through the casing to form an RS cavity through which cooling air flows, wherein the segment body includes a cavity for supplying cooling air introduced from the RS cavity to the channel.Type: ApplicationFiled: June 21, 2023Publication date: November 16, 2023Inventors: Yun Chang JANG, Simon HAUSWIRTH, Richard JONES
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Patent number: 11725538Abstract: A ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade existing inside the casing, the ring segment includes a segment body disposed inside the casing in a radial direction of the casing and having a channel through which cooling air flows, and a pair of segment protrusions protruding outward from the segment body, coupled to the inner circumferential surface of the casing, and spaced apart from each other along a flow direction of fluid flowing through the casing to form an RS cavity through which cooling air flows, wherein the segment body includes a cavity for supplying cooling air introduced from the RS cavity to the channel.Type: GrantFiled: January 27, 2022Date of Patent: August 15, 2023Assignee: DOOSAN ENERBNLITY CO., LTD.Inventors: Yun Chang Jang, Simon Hauswirth, Richard Jones
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Patent number: 11591922Abstract: A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.Type: GrantFiled: April 23, 2022Date of Patent: February 28, 2023Assignee: DOSAN ENERBILITY CO., LTD.Inventors: Yun Chang Jang, Andrey Sedlov, Thomas Kotteck
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Patent number: 11542834Abstract: A ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade disposed inside the casing, the ring segment includes a segment body disposed inside the casing in a radial direction of the casing and including a plurality of cooling channels through which cooling air flows, a pair of segment protrusions protruding outward from the segment body, coupled to the inner circumferential surface of the casing, and spaced apart from each other in a flow direction of fluid flowing through the casing to form an RS cavity into which cooling air is introduced, wherein when the segment body has a cross section along an imaginary plane including a radial straight line of the casing, the cooling channel is formed such that a width in a direction perpendicular to a radial direction of the casing is greater than a width in the radial direction of the casing.Type: GrantFiled: January 5, 2022Date of Patent: January 3, 2023Assignee: DOOSAN ENERBILITY CO., LTD.Inventor: Yun Chang Jang
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Publication number: 20220268173Abstract: A ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade disposed inside the casing, the ring segment includes a segment body disposed inside the casing in a radial direction of the casing and including a plurality of cooling channels through which cooling air flows, a pair of segment protrusions protruding outward from the segment body, coupled to the inner circumferential surface of the casing, and spaced apart from each other in a flow direction of fluid flowing through the casing to form an RS cavity into which cooling air is introduced, wherein when the segment body has a cross section along an imaginary plane including a radial straight line of the casing, the cooling channel is formed such that a width in a direction perpendicular to a radial direction of the casing is greater than a width in the radial direction of the casing.Type: ApplicationFiled: January 5, 2022Publication date: August 25, 2022Inventor: Yun Chang Jang
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Publication number: 20220268174Abstract: A ring segment and a turbomachine including the ring segment are provided. The ring segment installed on an inner circumferential surface of a casing and disposed to face an end of a blade existing inside the casing, the ring segment includes a segment body disposed inside the casing in a radial direction of the casing and having a channel through which cooling air flows, and a pair of segment protrusions protruding outward from the segment body, coupled to the inner circumferential surface of the casing, and spaced apart from each other along a flow direction of fluid flowing through the casing to form an RS cavity through which cooling air flows, wherein the segment body includes a cavity for supplying cooling air introduced from the RS cavity to the channel.Type: ApplicationFiled: January 27, 2022Publication date: August 25, 2022Inventors: Yun Chang JANG, Simon HAUSWIRTH, Richard JONES
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Patent number: 11421550Abstract: A ring segment, a turbine, and a gas turbine having improved cooling performance are provided. The ring segment may include a shielding wall mounted to a turbine casing which accommodates a turbine blade and configured to face an inner circumferential surface of the turbine casing, a first hook part and a second hook part configured to protrude from the shielding wall toward the turbine casing to be coupled to the turbine casing, a main cavity formed between the first hook part and the second hook part, a plurality of first cooling passages configured to connect the main cavity and first side surfaces facing each other of the shielding wall, a plurality of second cooling passages configured to extend in a direction crossing the first cooling passage and connect the main cavity and second side surfaces facing each other of the shielding wall, and a chamber configured to be connected to the first cooling passages.Type: GrantFiled: June 1, 2020Date of Patent: August 23, 2022Assignee: DOOSAN ENERBILITY CO., LTD.Inventors: Yun Chang Jang, Andrey Sedlov, Thomas Kotteck
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Publication number: 20220243603Abstract: A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.Type: ApplicationFiled: April 23, 2022Publication date: August 4, 2022Inventors: Yun Chang Jang, Andrey Sedlov, Thomas Kotteck
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Patent number: 11339677Abstract: A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.Type: GrantFiled: February 5, 2021Date of Patent: May 24, 2022Inventors: Yun Chang Jang, Andrey Sedlov, Thomas Kotteck
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Patent number: 11143043Abstract: A turbine vane improves cooling performance by guiding an impingement cooling fluid, introduced through a cooling hole of an inner sidewall provided inside the turbine vane, to flow while in contact with an inner surface of the turbine vane for a relatively long time. The turbine vane includes an outer sidewall configured to form an airfoil comprising a leading edge and a trailing edge; an inner sidewall disposed inside the outer sidewall to form a gap between the inner sidewall and an inner surface of the outer sidewall, the inner sidewall having a plurality of cooling holes communicating with the gap; and a plurality of spiral guides formed on the inner surface of the outer sidewall and disposed at positions facing the respective cooling holes, the plurality of spiral guides configured to guide a cooling fluid having passed through the cooling holes to impinge on the spiral guides.Type: GrantFiled: January 6, 2020Date of Patent: October 12, 2021Inventors: Yun Chang Jang, Andrey Sedlov, Thomas Kotteck
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Publication number: 20210246805Abstract: A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.Type: ApplicationFiled: February 5, 2021Publication date: August 12, 2021Inventors: Yun Chang Jang, Andrey Sedlov, Thomas Kotteck
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Publication number: 20200408108Abstract: A ring segment, a turbine, and a gas turbine having improved cooling performance are provided. The ring segment may include a shielding wall mounted to a turbine casing which accommodates a turbine blade and configured to face an inner circumferential surface of the turbine casing, a first hook part and a second hook part configured to protrude from the shielding wall toward the turbine casing to be coupled to the turbine casing, a main cavity formed between the first hook part and the second hook part, a plurality of first cooling passages configured to connect the main cavity and first side surfaces facing each other of the shielding wall, a plurality of second cooling passages configured to extend in a direction crossing the first cooling passage and connect the main cavity and second side surfaces facing each other of the shielding wall, and a chamber configured to be connected to the first cooling passages.Type: ApplicationFiled: June 1, 2020Publication date: December 31, 2020Inventors: Yun Chang JANG, Andrey SEDLOV, Thomas KOTTECK
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Patent number: 10865656Abstract: A turbine blade ring segment includes an inner panel mounted to an inner surface of a turbine casing, the inner panel including a plurality of flow holes for supplying cooling air from an outside of the turbine casing; and an outer panel disposed on one surface of the inner panel, the outer panel including a plurality of air passages communicating with the flow holes formed in the inner panel. The passages include a first flow passage formed in a central portion of the outer panel to guide the supplied cooling air in a flow direction of the combustion gas, a second flow passage formed in the outer panel separately from the first flow passage to guide the supplied cooling air in the flow direction of the combustion gas, and a third flow passage communicating with the second flow passage to feed the supplied cooling air to the second flow passage.Type: GrantFiled: September 12, 2018Date of Patent: December 15, 2020Assignee: Doosan Heavy Industries Construction Co., LtdInventor: Yun Chang Jang
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Patent number: 10837292Abstract: A turbine blade with a cooling structure includes a root member coupled to a turbine disk; an inlet formed in the root member to introduce cooling air to the turbine blade; an airfoil coupled to the root member, the airfoil having a suction-side surface and a pressure-side surface; and an internal cooling channel disposed between the suction-side and pressure-side surfaces of the airfoil and configured to pass the cooling air throughout the airfoil from the inlet to an ejection hole formed on an upper surface of the airfoil. The turbine blade may be included in a turbine of a gas turbine and is provided to blow air passing through the cooling channel toward a leading edge and an upper surface of the airfoil, thereby reducing heat load and thermal stress applied to the turbine blade and preventing the turbine blade from being damaged by the heat load or thermal stress.Type: GrantFiled: July 12, 2018Date of Patent: November 17, 2020Assignee: Doosan Heavy Industries Construction Co., LtdInventor: Yun Chang Jang
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Publication number: 20200271004Abstract: A turbine vane improves cooling performance by guiding an impingement cooling fluid, introduced through a cooling hole of an inner sidewall provided inside the turbine vane, to flow while in contact with an inner surface of the turbine vane for a relatively long time. The turbine vane includes an outer sidewall configured to form an airfoil comprising a leading edge and a trailing edge; an inner sidewall disposed inside the outer sidewall to form a gap between the inner sidewall and an inner surface of the outer sidewall, the inner sidewall having a plurality of cooling holes communicating with the gap; and a plurality of spiral guides formed on the inner surface of the outer sidewall and disposed at positions facing the respective cooling holes, the plurality of spiral guides configured to guide a cooling fluid having passed through the cooling holes to impinge on the spiral guides.Type: ApplicationFiled: January 6, 2020Publication date: August 27, 2020Inventors: Yun Chang JANG, Andrey Sedlov, Thomas Kotteck
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Patent number: 10662777Abstract: A structure for cooling turbine blades, and a turbine and gas turbine including the same, enhance efficiency in cooling turbine blades by improving the structures of a turbine disk and a retainer for securing a turbine blade. The structure includes a turbine blade connected to a turbine blade root; a turbine disk including a slot for receiving the turbine blade root, a cooling passage through which cooling air flows to the turbine blade root, and a branch passage communicating at one end with the cooling passage; and a retainer fixed to the turbine disk on each of opposite sides of the turbine blade to prevent separation of the turbine blade from the turbine disk, the fixed retainer having a chamber communicating with the other end of the branch passage so that the cooling air of the cooling passage is introduced into the chamber through the branch passage.Type: GrantFiled: July 5, 2018Date of Patent: May 26, 2020Assignee: Doosan Heavy Industries Construction Co., LtdInventor: Yun Chang Jang
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Publication number: 20190112944Abstract: A turbine blade ring segment includes an inner panel mounted to an inner surface of a turbine casing, the inner panel including a plurality of flow holes for supplying cooling air from an outside of the turbine casing; and an outer panel disposed on one surface of the inner panel, the outer panel including a plurality of air passages communicating with the flow holes formed in the inner panel. The passages include a first flow passage formed in a central portion of the outer panel to guide the supplied cooling air in a flow direction of the combustion gas, a second flow passage formed in the outer panel separately from the first flow passage to guide the supplied cooling air in the flow direction of the combustion gas, and a third flow passage communicating with the second flow passage to feed the supplied cooling air to the second flow passage.Type: ApplicationFiled: September 12, 2018Publication date: April 18, 2019Inventor: Yun Chang JANG