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公开(公告)号：US20240337228A1
公开(公告)日：2024-10-10
申请号：US18745410
申请日：2024-06-17
IPC分类号： F02K3/06
CPC分类号： F02K3/06 , F05D2200/14
摘要： A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes four rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 2.0-5.1. Additionally (or alternatively) the low-pressure turbine includes an area-EGT ratio within a range of 1.05-1.6.
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公开(公告)号：US20240280058A1
公开(公告)日：2024-08-22
申请号：US18649822
申请日：2024-04-29
摘要： A turbomachinery engine includes a fan assembly, a low-pressure turbine, and a gearbox. The fan assembly includes a plurality of fan blades. The low-pressure turbine includes 3-5 rotating stages. The low-pressure turbine includes an area ratio equal to the annular exit area of an aft-most rotating stage of the low-pressure turbine divided by the annular exit area of a forward-most rotating stage of the low-pressure turbine. In some instances, the area ratio is within a range of 3.1-5.1.
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公开(公告)号：US20240218803A1
公开(公告)日：2024-07-04
申请号：US18594065
申请日：2024-03-04
发明人： Bhaskar Nanda Mondal , John Joseph Rahaim , Thomas Moniz , Steven A. Ross , Joel Kirk , Scott Hunter , Daniel Fusinato
CPC分类号： F01D11/18 , F01D11/025 , F01D25/005 , F05D2240/11 , F05D2240/55 , F05D2260/30 , F05D2300/5021 , F05D2300/6033 , Y02T50/60
摘要： A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.
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公开(公告)号：US11859547B2
公开(公告)日：2024-01-02
申请号：US17826321
申请日：2022-05-27
发明人： Joseph G. Rose , Atanu Saha , Bhaskar Nanda Mondal , Craig W. Higgins , Darek Zatorski , Vaibhav Deshmukh M
CPC分类号： F02C7/06 , F02C3/06 , F05D2240/52 , F05D2260/15 , F05D2260/213 , F05D2260/232 , F05D2260/605 , F05D2260/607
摘要： A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.
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公开(公告)号：US11821326B2
公开(公告)日：2023-11-21
申请号：US17241242
申请日：2021-04-27
CPC分类号： F01D21/045 , F01D11/20 , F01D21/04 , F01D25/12 , F05D2220/32
摘要： A turbine containment system is provided. The turbine containment system includes a first containment member surrounding a portion of a turbine including a plurality of rotor disks and rotor blades; and a second containment member in communication with the first containment member, wherein the first containment member and the second containment member together contain each of the rotor disks and the rotor blades therein.
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公开(公告)号：US20230136238A1
公开(公告)日：2023-05-04
申请号：US18058036
申请日：2022-11-22
摘要： A turbomachine engine including an engine core including a high-pressure compressor, which has an exit stage having an exit stage diameter (DCORE), a high-pressure turbine, and a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, a power turbine in flow communication with the high-pressure turbine, and a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft. The low-pressure shaft has a length (LMSR) defined by an engine core length (LCORE) given by: LCORE=[m(20+m)*n(10+n)](1/100)*DCORE+CIS.
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公开(公告)号：US11549463B2
公开(公告)日：2023-01-10
申请号：US17181773
申请日：2021-02-22
摘要： Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.
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公开(公告)号：US20220349316A1
公开(公告)日：2022-11-03
申请号：US17864534
申请日：2022-07-14
发明人： Bhaskar Nanda Mondal , John Joseph Rahaim , Thomas Moniz , Steven A. Ross , Joel Kirk , Scott Hunter , Daniel Fusinato
摘要： A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flow path through the engine core.
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公开(公告)号：US11428160B2
公开(公告)日：2022-08-30
申请号：US17139138
申请日：2020-12-31
摘要： A gas turbine engine having an interdigitated turbine assembly including a first turbine rotor and a second turbine rotor, wherein a total number of stages at the interdigitated turbine assembly is between 3 and 8, and an average stage pressure ratio at the interdigitated turbine assembly is between 1.3 and 1.9. A gear assembly is configured to receive power from the interdigitated turbine assembly, and a fan assembly is configured to receive power from the gear assembly. The interdigitated turbine assembly and the gear assembly are together configured to allow the second turbine rotor to rotate at a second rotational speed greater than a first rotational speed at the first turbine rotor. The fan assembly and the gear assembly are together configured to allow the fan assembly to rotate at a third rotational speed less than the first rotational speed and the second rotational speed. The interdigitated turbine assembly, the gear assembly, and the fan assembly together have a maximum AN2 at the second turbine rotor between 30 and 90.
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公开(公告)号：US11231043B2
公开(公告)日：2022-01-25
申请号：US15900891
申请日：2018-02-21
发明人： Veeraraju Vanapalli , Bhaskar Nanda Mondal , Jagata Laxmi Narasimharao , Tsuguji Nakano , Subramanian Narayanan
摘要： The present disclosure is directed to a gas turbine engine including a compressor rotor. The compressor rotor includes a first stage compressor airfoil defined at an upstream-most stage of the compressor rotor. The first stage compressor airfoil defines a first stage pressure ratio of at least approximately 1.7 during operation of the gas turbine engine at a tip speed of at least approximately 472 meters per second.
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