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公开(公告)号：US10563672B2
公开(公告)日：2020-02-18
申请号：US15890866
申请日：2018-02-07
Applicant: United Technologies Corporation
Abstract: A high pressure compressor rotor stack includes a bore basket that includes a bore basket internal passage. A first plurality of rotor stages at least partially defines a forward rotor bore with a forward hub structure and the bore basket. A second plurality of rotor stages at least partially defines an aft rotor bore with an aft hub structure and the bore basket.
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公开(公告)号：US10808544B1
公开(公告)日：2020-10-20
申请号：US15868181
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Xuedong Zhou , Evan K. Fink , Joseph C. Straccia , Joseph Wieser , Konstantinos Panagiotis Giannakopoulos
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.35-4.65 inch (110.5-118.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.45-2.75 inch (62.2-69.9 mm). The airfoil element includes at least two of a first mode with a frequency of 255±10% Hz, a second mode with a frequency of 818±10% Hz, a third mode with a frequency of 1439±10% Hz, a fourth mode with a frequency of 2035±10% Hz, a fifth mode with a frequency of 3033±10% Hz and a sixth mode with a frequency of 3740±10% Hz.
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公开(公告)号：US10774742B2
公开(公告)日：2020-09-15
申请号：US15927659
申请日：2018-03-21
Applicant: United Technologies Corporation
Abstract: A compressor rotor includes a first disk and a conical section connected to the first disk. The conical section includes at least one flow hole. A bore cavity is defined between the conical section and the first disk. The bore cavity is arranged in fluid communication with the at least one flow hole. An anti-vortex tube is disposed within the at least one flow hole of the conical section and includes at least one feature arranged in contact with a surface of the conical section to restrict movement of the anti-vortex tube out of engagement with the conical section.
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公开(公告)号：US20190292981A1
公开(公告)日：2019-09-26
申请号：US15927659
申请日：2018-03-21
Applicant: United Technologies Corporation
Abstract: A compressor rotor includes a first disk and a conical section connected to the first disk. The conical section includes at least one flow hole. A bore cavity is defined between the conical section and the first disk. The bore cavity is arranged in fluid communication with the at least one flow hole. An anti-vortex tube is disposed within the at least one flow hole of the conical section and includes at least one feature arranged in contact with a surface of the conical section to restrict movement of the anti-vortex tube out of engagement with the conical section.
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公开(公告)号：US20190242407A1
公开(公告)日：2019-08-08
申请号：US15890866
申请日：2018-02-07
Applicant: United Technologies Corporation
CPC classification number: F04D29/584 , F01D5/082 , F01D5/085 , F01D25/125 , F02C3/04 , F04D19/02 , F04D29/102 , F05D2220/323 , F05D2240/20 , F05D2260/205
Abstract: A high pressure compressor rotor stack includes a bore basket that includes a bore basket internal passage. A first plurality of rotor stages at least partially defines a forward rotor bore with a forward hub structure and the bore basket. A second plurality of rotor stages at least partially defines an aft rotor bore with an aft hub structure and the bore basket.
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Patent Agency Ranking
公开(公告)号：US10760429B1
公开(公告)日：2020-09-01
申请号：US15868312
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Xuedong Zhou , Evan K. Fink , Joseph C. Straccia , Joseph Wieser , Konstantinos Panagiotis Giannakopoulos
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 3.45-3.75 inch (87.6-95.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.55-1.85 inch (39.4-47.0 mm). The airfoil element includes at least two of a first mode with a frequency of 424±10% Hz, a second mode with a frequency of 1401±10% Hz, a third mode with a frequency of 1770±10% Hz, a fourth mode with a frequency of 3336±10% Hz, a fifth mode with a frequency of 3378±10% Hz and a sixth mode with a frequency of 4141±10% Hz.
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公开(公告)号：US11346252B2
公开(公告)日：2022-05-31
申请号：US16458729
申请日：2019-07-01
Applicant: United Technologies Corporation
Inventor： Konstantinos Panagiotis Giannakopoulos , Thomas Carlsen
Abstract: A case assembly for a gas turbine engine includes a case extending circumferentially about an engine central longitudinal axis and two or more components installed in the case at different axial and/or radial locations. A retainer is installed at a circumferential end of the case, the retainer configured to circumferentially retain the two or more components at the case. A circumferential retainer of a case assembly of a gas turbine engine includes a retainer pin configured for installation in retaining feature of a circumferential end of a case, and one or more retainer arms extending from the retainer pin. The one or more retainer arms are configured to extend at least partially across two or more components installed in the case at different axial and/or radial locations to circumferentially retain the two or more components at the case.
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公开(公告)号：US11236616B1
公开(公告)日：2022-02-01
申请号：US15868499
申请日：2018-01-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kurt R. Heinemann , Sumin Tao , Christopher B. Jelks , Xuedong Zhou , Mark David Ring , Konstantinos Panagiotis Giannakopoulos , Kate Hudon , John Joseph Papalia
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 4.47-4.77 inch (113.5-121.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297±10% Hz, a second mode with a frequency of 1035±10% Hz, a third mode with a frequency of 1488±10% Hz, a fourth mode with a frequency of 1524±10% Hz, a fifth mode with a frequency of 2855±10% Hz and a sixth mode with a frequency of 4462±10% Hz.
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公开(公告)号：US20210003035A1
公开(公告)日：2021-01-07
申请号：US16458729
申请日：2019-07-01
Applicant: United Technologies Corporation
Inventor： Konstantinos Panagiotis Giannakopoulos , Thomas Carlsen
Abstract: A case assembly for a gas turbine engine includes a case extending circumferentially about an engine central longitudinal axis and two or more components installed in the case at different axial and/or radial locations. A retainer is installed at a circumferential end of the case, the retainer configured to circumferentially retain the two or more components at the case. A circumferential retainer of a case assembly of a gas turbine engine includes a retainer pin configured for installation in retaining feature of a circumferential end of a case, and one or more retainer arms extending from the retainer pin. The one or more retainer arms are configured to extend at least partially across two or more components installed in the case at different axial and/or radial locations to circumferentially retain the two or more components at the case.
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公开(公告)号：US10815785B1
公开(公告)日：2020-10-27
申请号：US15869119
申请日：2018-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Kurt R. Heinemann , Sumin Tao , Christopher B. Jelks , Xuedong Zhou , Mark David Ring , Konstantinos Panagiotis Giannakopoulos , Kate Hudon , John Joseph Papalia
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 2.99-3.29 inch (75.9-83.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430±10% Hz, a second mode with a frequency of 1459±10% Hz, a third mode with a frequency of 2036±10% Hz, a fourth mode with a frequency of 3615±10% Hz, a fifth mode with a frequency of 4722±10% Hz and a sixth mode with a frequency of 5591±10% Hz.
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