| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | 주조용 중자 성형장치 | KR1020210126986 | 2021-09-27 | KR102362129B1 | 2022-02-14 | |
| 82 | 경사진 원통형 중공부를 갖는 주물 제작 방법 및 그것을 이용한 선박용 어퍼 케스팅 제작 방법 | KR1020130120677 | 2013-10-10 | KR101503157B1 | 2015-03-16 | 정원종; 서영교 |
| 기울기를 갖는 원통형 중공부가 형성된 주물을 제작하는 방법이 개시된다. 방법은 어퍼 케스팅의 형상을 갖는 주형 내에 외면이 경사진 코어를 용강의 주입 방향과 나란하게 배치하여 경사진 원통형 중공부를 갖는 선박용 어퍼 케스팅이 제작된다.
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| 83 | 사형의 쇳물 주입구 성형방법 및 그 성형장치 | KR1020130038826 | 2013-04-09 | KR1020140122127A | 2014-10-17 | 이지환 |
| 본 발명은 주물사(鑄物砂)를 단단하게 다져서 제조되는 사형(sand mold, 砂型)의 내부에 쇳물을 주입하기 위한 주입구를 작업자가 수작업을 통해 성형하지 않고 연속 자동화 공정에 의해 사형(sand mold, 砂型)의 쇳물 주입구가 자동으로 성형 되도록 함으로써 주입구 성형에 소요되는 인적, 물적 자원의 절약과 동시에 주입구 성형과정에서 사형(sand mold, 砂型)이 파손되지 않도록 하는 사형의 쇳물 주입구 성형방법 및 그 성형장치에 관한 것으로,
수직방향으로 돌출된 구조를 갖는 주입구 성형용 가이드핀(20)을 금형(910)의 상단 면과 일체형이 되도록 고정시키는 가이드핀 고정단계(S100)와, 상기 가이드핀(20)에 대응하는 핀삽입홀(31)이 일체형의 구조로 구성된 가이드판(30)을 상부 가압블록(610)에 장착 고정시키는 가이드판 고정단계(S200)와, 상기 금형(910)과 상부 가압블록(610)에 가이드핀(20)과, 가이드판(30)이 장착 고정된 상태에서 사형 틀(1)의 내부에 주물사(50) 공급이 완료되면, 사형 틀(1)에 충진 된 주물사를 단단하게 다져주기 위해 사형 틀(1)을 중심으로 상측에서 하강하는 상부 가압블록(610)과, 하측에서 상승하는 하부 가압블록(620)을 개별 또는 동시에 승강시켜 사형 틀(1)을 가압하되, 가압과 동시에 사형 틀(1)의 내부에 제조되는 사형(砂型)의 일측에 쇳물 주입구(40)가 성형 되도록 하는 주입� �� 성형단계(S300)로 이루어진다. |
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| 84 | 반경방향 외측으로 확장된 단부를 갖는 관형제품의 주형성형용 원형과 그 원형을 이용한 주형성형장치 | KR1019920011851 | 1992-07-03 | KR100091719B1 | 1995-11-15 | 김제범 |
| 85 | 반경방향 외측으로 확장된 단부를 갖는 관형제품의 주형성형용 원형과 그 원형을 이용한 주형성형장치 | KR1019920011851 | 1992-07-03 | KR1019950005287B1 | 1995-05-23 | 김제범 |
| 내용 없음. | ||||||
| 86 | AIRFOIL FOR A GAS TURBINE ENGINE AND CORRESPONDING CORE STRUCUTURE FOR MANUFACTURING AN AIRFOIL | EP18198488.1 | 2018-10-03 | EP3467267B1 | 2023-05-10 | CLUM, Carey; JENNINGS, Timothy J. |
| 87 | AIRFOIL FOR A GAS TURBINE ENGINE AND CORRESPONDING CORE STRUCTURE FOR MANUFACTURING AN AIRFOIL | EP18198427.9 | 2018-10-03 | EP3467263B1 | 2023-05-10 | PROPHETER-HINCKLEY, Tracy A.; CLUM, Carey; JENNINGS, Timothy J. |
| 88 | AIRFOIL FOR A GAS TURBINE ENGINE AND CORRESPONDING CORE STRUCTURE FOR MANUFACTURING AN AIRFOIL | EP18198478.2 | 2018-10-03 | EP3467265B1 | 2023-01-18 | PROPHETER-HINCKLEY, Tracy A.; CLUM, Carey; JENNINGS, Timothy J. |
| 89 | AIRFOIL FOR A GAS TURBINE ENGINE AND CORRESPONDING CORE STRUCUTURE FOR MANUFACTURING AN AIRFOIL | EP18198465.9 | 2018-10-03 | EP3467264B1 | 2022-12-14 | PROPHETER-HINCKLEY, Tracy A.; CLUM, Carey; JENNINGS, Timothy J. |
| 90 | TURBINE AEROFOIL | EP18206713.2 | 2018-11-16 | EP3653839A1 | 2020-05-20 | Viano, Andrea |
A turbine aerofoil (100) for a turbo machine. The aerofoil (100) comprises a main body portion (200) defined by a leading edge (220) and a trailing edge (230). The main body portion (200) has a flow inlet (240) and flow outlet (250). A leading edge cooling chamber (260) is defined within the leading edge (220) of the main body portion (200). The leading edge cooling chamber (260) extends between the flow inlet (240) and the flow outlet (250). The leading edge cooling chamber (260) comprises a first sub chamber (280) and a second sub chamber (300), the first sub chamber (280) being in flow series between the flow inlet (240) and the second sub chamber (300). The second sub chamber (300) is in flow series between first sub chamber (280) and the flow outlet (250). The first sub chamber (280) is divided into a first section (292) and second section (294) in fluid communication via an intermediate section (296). The first section (292) of the first sub chamber (280) and the second sub chamber (300) extend in a first column (310) along at least part of the leading edge (220). The second section (294) extends in a second column (320) provided between the first column (310) and the trailing edge (230). The first sub chamber (280) is in flow communication with the second sub chamber (300) via a flow passage (400) which extends between the second section (294) of the first sub chamber (280) and the second sub chamber (300).
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| 91 | AIRFOIL FOR A GAS TURBINE ENGINE AND CORRESPONDING CORE STRUCUTURE FOR MANUFACTURING AN AIRFOIL | EP18198497.2 | 2018-10-03 | EP3467268A1 | 2019-04-10 | CLUM, Carey; JENNINGS, Timothy J.; PROPHETER-HINCKLEY, Tracy A. |
An airfoil for a gas turbine engine, comprising an airfoil body having a first (1502) and a second core cavities (1504) adjacent each other, with the second core cavity defined by a first cavity wall (1512), a second cavity wall (1514), a first exterior wall (1516), and a second exterior wall (1518). The first cavity wall is located between the second and first core cavites and the first and second exterior walls. The first cavity wall includes a first surface (1524) angled toward the first exterior wall and a second surface (1526) angled toward the second exterior wall. At least one first cavity impingement hole (1520, 1522) is formed within the first surface with a first impingement flow flowing from the first core cavity through the at least one first cavity impingement hole to impinge upon the first exterior wall and forms a first high momentum jet of impingement air thereon. A core structure for manufacturing an airfoil for a gas turbine engine comprises adjacent first and second core cavity cores to form first and second core cavites, with a first cavity wall is located between the core cavity cores. A space between the cavity cores that defines the first cavity wall includes first and second portions to form first and second surfaces that are angled toward first and second exterior walls. At least one first cavity impingement stem extends between the first and second core cavity cores to form least one first cavity impingement hole.
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| 92 | LEADING EDGE HYBRID CAVITIES AND CORES FOR AIRFOILS OF GAS TURBINE ENGINE | EP18159671.9 | 2018-03-02 | EP3399145A3 | 2018-12-12 | CLUM, Carey; MONGILLO, Dominic J. |
The present invention is related to an airfoil (200) comprising a leading edge hybrid skin core cavity (202) formed within the airfoil extending from the root (200b) to the tip (200a) along a leading edge (206) of the airfoil (200). The cavity (202) having a hot wall (208) and a cold wall (210) has a variable height-to-width ratio (H/W) in a direction from the tip (200a) with a first hot and cold wall geometric profile (208a, 210a) to the root (200b) having a second hot and cold wall geometric profile (208b, 210b). Thus, the aspect ratio, i.e. heigth-to-width ratio, varies along the airfoil span from a first aspect ratio (H1/W1) to a second, different aspect ratio (H2/W2). This geomtric cavity design significantly improves internal heat transfer characteristics, hence, enabling high internal convective heat transfer coefficients due to high flow per unit area.
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| 93 | LEADING EDGE HYBRID CAVITIES AND CORES FOR AIRFOILS OF GAS TURBINE ENGINE | EP18159671.9 | 2018-03-02 | EP3399145A2 | 2018-11-07 | CLUM, Carey; MONGILLO, Dominic J. |
The present invention is related to an airfoil (200) comprising a leading edge hybrid skin core cavity (202) formed within the airfoil extending from the root (200b) to the tip (200a) along a leading edge (206) of the airfoil (200). The cavity (202) having a hot wall (208) and a cold wall (210) has a variable height-to-width ratio (H/W) in a direction from the tip (200a) with a first hot and cold wall geometric profile (208a, 210a) to the root (200b) having a second hot and cold wall geometric profile (208b, 210b). Thus, the aspect ratio, i.e. heigth-to-width ratio, varies along the airfoil span from a first aspect ratio (H1/W1) to a second, different aspect ratio (H2/W2). This geomtric cavity design significantly improves internal heat transfer characteristics, hence, enabling high internal convective heat transfer coefficients due to high flow per unit area.
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| 94 | Aerofoil and method of manufacture | US16191668 | 2018-11-15 | US10844732B2 | 2020-11-24 | Adrian L. Harding |
| A method of manufacturing the aerofoil, and an aerofoil. The method includes: casting a first body portion having a passage passing there-through; casting a second body portion; and joining the first body portion and the second body portion to form the aerofoil. The passage extends from an opening at a first end at or near a leading edge to an opening at a second end at or near a trailing edge. The passage is formed during the casting process by a core; and the core is supported at the first and second ends through the respective openings of the passage. | ||||||
| 95 | Leading edge hybrid cavities and cores for airfoils of gas turbine engine | US15584119 | 2017-05-02 | US10830049B2 | 2020-11-10 | Carey Clum; Dominic J. Mongillo |
| Airfoils having a leading edge, a trailing edge, a first end, and a second end with a leading edge hybrid skin core cavity formed within the airfoil extending from the first end to the second end proximate the leading edge, the cavity having a hot wall and a cold wall. The cavity has a variable height-to-width ratio in a direction from the first end to the second end, with a first aspect ratio proximate the first end and a second aspect ratio proximate the second end with the height defined as a maximum distance between the hot wall and the cold wall and the width is defined as an arc length of the cold wall. | ||||||
| 96 | Airfoil having fluidly connected hybrid cavities | US15723461 | 2017-10-03 | US10760432B2 | 2020-09-01 | Carey Clum; Timothy J. Jennings |
| Airfoils having a leading edge and a trailing edge, with a plurality of cavities therein including a leading edge hybrid cavity extending in a radial direction between a first end and a second end of the airfoil body along the leading edge. An airfoil side hybrid cavity is located toward the trailing edge relative to the leading edge hybrid cavity and positioned adjacent a side wall of the airfoil body. The airfoil side hybrid cavity extends in a radial direction between the first end and the second end and a divider rib extends radially between the first end and the second end along the side wall of the airfoil between the airfoil side hybrid cavity and the leading edge hybrid cavity. At least one first cross-over hole is formed within the divider rib to fluidly connect the airfoil side hybrid cavity to the leading edge hybrid cavity. | ||||||
| 97 | Airfoil having internal hybrid cooling cavities | US15723486 | 2017-10-03 | US10704398B2 | 2020-07-07 | Tracy A. Propheter-Hinckley; Carey Clum; Timothy J. Jennings |
| Airfoil bodies having a first core cavity and a second core cavity located within the airfoil body and adjacent the first core cavity, wherein the second core cavity is defined by a first cavity wall, a second cavity wall, a first exterior wall, and a second exterior wall, wherein the first cavity wall is located between the first and second core cavities. The first cavity wall includes a first surface angled toward the first exterior wall and a second surface angled toward the second exterior wall. At least one first cavity impingement hole is formed within the first surface. At least one circuit exit is located in the first exterior wall, the at least one circuit exit arranged to expel air from the second core cavity through the first exterior wall. | ||||||
| 98 | Method of manufacturing a heat exchanger | US508532 | 1983-06-28 | US4558695A | 1985-12-17 | Takahiro Kumazawa; Yoshihiro Nakamura; Toshihisa Izawa |
| A heat exchanger such as a radiator for an automotive engine is produced by fixing lengths of flattened tubes and corrugated fins to each other by brazing within a furnace. The flattened tube is formed by bending a strip and welding the opposing edges of the bent strip to each other to form a tube of a substantially circular cross-section, and applying pressure to the tube along the weld line to form the flattened tube while depressing the tube wall along the weld line to form an elongated recess or groove along the weld line. Then, a brazing material is applied to the outer surfaces of the flattened tube to cover and fill up any minute weld defects which may exist in the flattened tube whereby the weld defects are repaired. | ||||||
| 99 | Method and apparatus for centrifugal casting | US778705 | 1977-03-17 | US4124056A | 1978-11-07 | Charles H. Noble |
| Tubular metal articles are produced by centrifugal casting in a rotary metal mold lined by centrifugally distributing a quantity of a dry finely particulate free flowing refractory material on the active mold surface with the quantity being in excess of that required for the lining, densifying the layer by rotating the mold at a rate such that the refractory layer is subjected to centrifugal force adequate to establish an equivalent specific gravity of at least 7.5, determined by multiplying the actual specific gravity of the refractory material by the number of gravities of centrifugal force, contouring the densified layer and removing the excess refractory material, rotating the mold at the casting rate and then introducing the molten metal for casting while continuing to rotate the mold at least that rate. Articles so cast have relatively smooth outer surfaces which require only finish machining. The invention employs no additives and thus eliminates the need for venting the metal mold, provides a relatively thick lining of predetermined insulating capability so as to control the grain structure of the cast metal, eliminates the usual end cores, and allows the refractory material to be recycled. The invention is particularly useful for casting articles, such as cylinder liner blanks, from grey iron, such articles having an outer enlargement, typically a transverse outer end flange. Cast according to the invention, such articles have Type A graphite throughout the entire inner surface and for at least a substantial portion of the thickness of the flange or other outer enlargement. | ||||||
| 100 | Apparatus for forming foundry molds for casting pipes | US44171565 | 1965-03-22 | US3255497A | 1966-06-14 | JOHNSTON LOYAL L |
