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公开(公告)号：US11982189B2
公开(公告)日：2024-05-14
申请号：US17339604
申请日：2021-06-04
CPC分类号： F01D11/20 , F02C9/00 , F05D2220/32 , F05D2270/01
摘要： According to an aspect, a gas turbine engine includes a turbine section with a turbine case and a plurality of turbine blades within the turbine case. The gas turbine engine also includes an active clearance control system with an active clearance control cooling air supply, a valve pneumatically coupled to the active clearance control cooling air supply, and a controller. The controller is configured to determine an active cooling control schedule adjustment based on a condition of the gas turbine engine, operate the active clearance control system according to an active cooling control schedule as modified by the active cooling control schedule adjustment, apply a decay function to the active cooling control schedule adjustment to reduce an effect on the active cooling control schedule adjustment, and resume operating the active clearance control system according to the active cooling control schedule based on an active cooling control condition being met.
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公开(公告)号：US20240018878A1
公开(公告)日：2024-01-18
申请号：US17900513
申请日：2022-08-31
发明人： Anusrita RAYCHAUDHURI , Ravindra Shankar GANIGER , Bhanu BATTU , Richa AWASTHI , Nilesh VAROTE , Vidyashankar BURAVALLA
IPC分类号： F01D11/20
CPC分类号： F01D11/20 , F05D2220/32
摘要： Variable sleeve clearance control systems for gas turbine engines are disclosed. An example variable sleeve clearance control system for a gas turbine engine includes a sleeve comprising a first end and a second end, the first end of the sleeve coupled to a first spring that biases the sleeve inward, and the second end of the sleeve coupled to a second spring that biases the sleeve outward, a proximity sensor to measure a clearance width, and a controller for each of the first and second springs, the controller to obtain the measured clearance width from the proximity sensor and determine a response of the first and second springs.
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公开(公告)号：US11808217B2
公开(公告)日：2023-11-07
申请号：US17439172
申请日：2020-03-05
CPC分类号： F02C9/28 , F01D11/20 , F05D2220/70 , F05D2270/112
摘要： A method for regulating the temperature of the exhaust gases of a turbomachine, the method including regulation of the injection of fuel into a combustion chamber of the turbomachine so that the turbomachine generates a target thrust; regulation of the injection of mechanical power by an electric motor onto a shaft driven in rotation by a turbine, the electric motor being activated when a clearance between a casing and the blades of the turbine exceeds a threshold value.
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公开(公告)号：US20220213801A1
公开(公告)日：2022-07-07
申请号：US17142047
申请日：2021-01-05
发明人： Taehong Kim , Aaron J. Sentis
IPC分类号： F01D11/20
摘要： Methods and apparatus for real-time clearance assessment using a pressure measurement are disclosed. An example method includes determining a first and a second static pressure measurement at a first measurement location and a second measurement location, respectively, relative to the blade tip clearance, determining a normalized pressure measurement using the first and second static pressure measurements, generating a conversion curve to correlate the normalized pressure measurement with a clearance measurement, and adjusting active clearance control of the blade tip clearance based on a comparison of real-time in-flight pressure measurements to the conversion curve.
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公开(公告)号：US11268445B2
公开(公告)日：2022-03-08
申请号：US16613275
申请日：2018-05-10
摘要： In a gas turbine, a plurality of blade ring parts each include a plurality of first cooling flow passages, a plurality of second cooling flow passages, and a return flow passage. The first cooling flow passages are disposed on the outer side in a radial direction centering on a rotation axis, extend in an axial direction, and are disposed aligned in an axial rotation direction. The second cooling flow passages are disposed on an inner side in the radial direction with respect to the first cooling flow passages, extend in the axial direction, and are disposed aligned in the axial rotation direction. The return flow passage connects end parts of each of the first cooling flow passages and the second cooling flow passages on the same side in the axial direction with each other.
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公开(公告)号：US11073022B2
公开(公告)日：2021-07-27
申请号：US16083989
申请日：2017-03-22
发明人： Reiner Anton , Georg Bostanjoglo , Arturo Flores Renteria , Jacek Grodzki , Robert Herfurth , Eckart Schumann , Silke Settegast , Rüstü Söl
摘要： A turbine blade has a blade tip, a cooling structure with cooling channels which are designed to have cooling fluid passed through them in order to cool the turbine blade during operation, an end section at a lower level than that of the blade tip, and an outer wall section extending up to the blade tip. The cooling structure is formed between the end section and the blade tip. A method produces a cooling structure of this type.
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公开(公告)号：US11050011B2
公开(公告)日：2021-06-29
申请号：US15844711
申请日：2017-12-18
发明人： Sameh Dardona , Andrew Consiglio
IPC分类号： H01L41/113 , F01D17/02 , H04B7/24 , F01D17/04 , F01D11/20 , H01L41/08 , G01H11/08 , G01L1/16 , G01L9/08
摘要： A sensor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a substrate layer formed on a localized surface of a rotatable gas turbine engine component, and at least one pair of transducers deposited on the substrate layer.
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公开(公告)号：US20210087948A1
公开(公告)日：2021-03-25
申请号：US17016749
申请日：2020-09-10
发明人： Gabriel L. Suciu
摘要： An embodiment of a turbine engine outer case ring assembly includes a substantially circular first main body and a sealant layer covering at least a main gas-facing surface of the inner gas path side, the sealant layer having at least one coating sufficient to prevent infiltration of working gas into pores of the main body.
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9.发明授权公开(公告)号：US10934972B2
公开(公告)日：2021-03-02
申请号：US16039929
申请日：2018-07-19
发明人： Michael Hrach , Michael M. Romero
IPC分类号： F02C7/32 , F02K5/00 , F01D11/16 , F01D13/00 , F02C3/04 , F02K3/06 , F01D17/02 , F02C7/36 , F02C7/275 , F01D11/20 , F01D15/10 , F01D11/22
摘要： A method of maintaining rotor tip clearance and compressor operational line during a transient operation of a gas turbine engine is disclosed. In various embodiments, the method includes applying high spool auxiliary power to a high speed spool for a first time period, applying low spool auxiliary power to a low speed spool for a second time period, sensing one or more operational parameters of the gas turbine engine during the transient operation, and ceasing application of power to the high speed spool, based on the one or more operational parameters.
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公开(公告)号：US10823114B2
公开(公告)日：2020-11-03
申请号：US16535930
申请日：2019-08-08
摘要： The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section, a gearbox proximate to the turbine section, and a driveshaft. The turbine section includes a first rotating component interdigitated with a second rotating component along the longitudinal direction. The first rotating component includes an outer shroud defining a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction and one or more connecting airfoils coupling the outer shroud to a radially extended rotor. The second rotating component includes an inner shroud defining a plurality of inner shroud airfoils extended outward of the inner shroud along the radial direction. The second rotating component is coupled to an input shaft connected to an input gear of the gearbox. The driveshaft is extended in the longitudinal direction and is connected to an output gear of the gearbox. The first rotating component is coupled to the driveshaft.
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