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公开(公告)号：US10815886B2
公开(公告)日：2020-10-27
申请号：US15625101
申请日：2017-06-16
发明人： Christopher James Kroger , Brandon Wayne Miller , Trevor Wayne Goerig , David William Crall , Tsuguji Nakano , Jeffrey Donald Clements , Bhaskar Nanda Mondal
IPC分类号： F02C7/05 , F02C3/04 , F02K3/06 , F04D29/52 , F04D29/68 , F02C7/04 , F04D29/54 , F02C7/057 , F02C7/042
摘要： A gas turbine engine includes a compressor section and a turbine section. The turbine section includes a drive turbine and is located downstream of the compressor section. The gas turbine engine also includes a fan mechanically coupled to and rotatable with the drive turbine such that the fan is rotatable by the drive turbine at the same rotational speed as the drive turbine, the fan defining a fan pressure ratio and including a plurality of fan blades, each fan blade defining a fan tip speed. During operation of the gas turbine engine at a rated speed, the fan pressure ratio of the fan is less than 1.5 and the fan tip speed of each of the fan blades is greater than 1,250 feet per second.
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公开(公告)号：US10316681B2
公开(公告)日：2019-06-11
申请号：US15168581
申请日：2016-05-31
发明人： Jagata Laxmi Narasimharao , Thomas Ory Moniz , Mohamed Musthafa Thoppil , Bhaskar Nanda Mondal , Atanu Saha
摘要： A turbine assembly includes a rotor assembly including a shaft coupled to a plurality of rotor stages including a plurality of turbine blades. The shaft and the plurality of turbine blades define a wheelspace therein. The turbine assembly further includes a plurality of seals in series, at least one seal of the plurality of seals is coupled between a static support member and a respective rotor stage such that a plurality of turbine cavities in series are defined within the wheelspace. Each turbine cavity of the plurality of turbine cavities defined by the plurality of seals receives a pressurized fluid flow that applies an axially aft force to the respective rotor stage of the plurality of rotor stages that at least partially reduces net rotor thrust generated by the rotor assembly during operation, the pressurized fluid flow further provides turbine purge within the wheel space.
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公开(公告)号：US20170268535A1
公开(公告)日：2017-09-21
申请号：US15447565
申请日：2017-03-02
发明人： Bhaskar Nanda Mondal , Kenneth Edward Seitzer , Monty Lee Shelton , Thomas Ory Moniz , Atanu Saha
CPC分类号： F04D29/642 , F01D11/24 , F02K3/06 , F04D19/02 , F04D29/5846 , F04D29/5853 , F05D2220/32 , F05D2260/201 , Y02T50/671
摘要： The turbomachine includes a compressor, an inner annular casing, and an outer annular casing. The inner annular casing and the outer annular casing define at least one cavity therebetween. The clearance control system includes a manifold system including at least one conduit disposed within the cavities and configured to channel a flow of cooling fluid between the cavities. The clearance control system also includes an impingement system including a header and at least one plenum configured to channel the flow of cooling fluid to the inner annular casing. The conduits configured to channel the flow of cooling fluid to the impingement system. The clearance control system further includes a channel system including at least one channels configured to channel the flow of cooling fluid to the turbomachine. The channels are configured to control the flow of cooling fluid to the manifold system.
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公开(公告)号：US12123358B2
公开(公告)日：2024-10-22
申请号：US18651425
申请日：2024-04-30
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：US20240280055A1
公开(公告)日：2024-08-22
申请号：US18430269
申请日：2024-02-01
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：US12012901B1
公开(公告)日：2024-06-18
申请号：US18318604
申请日：2023-05-16
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 2.0-6.5. Additionally (or alternatively) the low-pressure turbine includes an area-EGT ratio within a range of 1.3-1.6.
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公开(公告)号：US12000308B2
公开(公告)日：2024-06-04
申请号：US17893747
申请日：2022-08-23
CPC分类号： F01D5/3053 , F01D5/225 , F05D2220/32 , F05D2240/30
摘要： A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.
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公开(公告)号：US20230272744A1
公开(公告)日：2023-08-31
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：US11280219B2
公开(公告)日：2022-03-22
申请号：US16697350
申请日：2019-11-27
发明人： Shashank Suresh Puranik , Bhaskar Nanda Mondal , Richard Schmidt , Peeyush Pankaj , Narayanan Payyoor
摘要： A rotor support system for a gas turbine engine includes a rotatable drum rotor and a non-rotatable support casing. The rotor support system includes a bearing assembly configured for positioning between the rotatable drum rotor and the non-rotatable support casing. The bearing assembly includes, at least, a stationary support frame and a rotatable race. Further, the rotatable race is configured to engage the rotatable drum rotor at separate and discrete locations that are circumferentially spaced apart around the rotatable drum rotor.
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公开(公告)号：US11193720B2
公开(公告)日：2021-12-07
申请号：US16828186
申请日：2020-03-24
摘要： A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path. The heat absorption device is configured to exchange heat between the phase change material and the input bleed flow to generate an output bleed flow of a different temperature than the input bleed flow and discharge the output bleed flow to a second predefined location different from the first predefined location.
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