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公开(公告)号：US09777632B2
公开(公告)日：2017-10-03
申请号：US14889752
申请日：2013-05-07
Applicant: General Electric Company
Inventor： Randall Maurice Prather , Neil Fraser Cunningham , Junhaur Jih , Erich Alois Krammer , Sesha Subramanian
CPC classification number: F02C7/047 , F01D25/02 , F05D2260/201 , Y02T50/672 , Y02T50/675
Abstract: Splitter apparatus for gas turbine engines are disclosed. An example splitter apparatus may include a splitter including an annular outer wall substantially defining a convex leading edge; an annular splitter support positioned radially within the outer and including a forward end disposed substantially against a splitter inner; and an annular first bulkhead spanning between the outer wall and the splitter support. The outer wall, the splitter support, and the first bulkhead may define a generally annular splitter plenum. The forward end of the splitter support may include spaced apart, radially oriented metering slots. The outer wall may include an inner portion disposed radially inward from the splitter inner surface extending aft and including spaced-apart exit slots. The splitter plenum, the metering slots, and the exit slots may conduct airflow from the plenum, through the metering slots against the splitter inner surface, and through the exit slots.
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公开(公告)号：US20170138262A1
公开(公告)日：2017-05-18
申请号：US14940251
申请日：2015-11-13
Applicant: General Electric Company
Inventor： Satoshi Atsuchi , Erich Alois Krammer , Corey Bourassa , Byron Andrew Pritchard , Mehmet Dede
CPC classification number: F02C7/052 , B01D45/04 , F02C7/12 , F05D2260/202 , F05D2260/607 , Y02T50/671 , Y02T50/676
Abstract: A particle separator for a turbomachine includes a first portion including a first end and a second end opposite the first end. The turbomachine includes a first wall and a second wall defining a primary fluid passage. The first wall further defines an auxiliary fluid passage. The first end is coupled to the first wall. The second end extends from the first wall into the at least one primary fluid passage and extends in a direction defined by the fluid flow through the primary fluid passage. The second end and the first wall define a fluid diversion passage coupled in flow communication with the primary fluid passage and the auxiliary fluid passage. The fluid diversion passage is configured to divert fluid from the primary fluid passage to the auxiliary fluid passage in a direction at least partially opposed to the fluid flow through the primary fluid passage.
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公开(公告)号：US20170122209A1
公开(公告)日：2017-05-04
申请号：US14932162
申请日：2015-11-04
Applicant: General Electric Company
Inventor： Mehmet Muhittin Dede , Satoshi Atsuchi , Byron Andrew Pritchard , Erich Alois Krammer , Giridhar Jothiprasad , Shourya Prakash Otta , Corey Bourassa
CPC classification number: F02C7/18 , B01D45/16 , F01D5/081 , F01D9/041 , F01D9/065 , F02C6/08 , F02C7/052 , F02C9/18 , F04D29/542 , F04D29/584 , F05D2240/124 , F05D2250/51 , F05D2260/232 , F05D2260/607 , Y02T50/671 , Y02T50/676
Abstract: The invention relates to a gas turbine engine comprising a casing having a compressor section, combustion section and turbine section, axially arranged in a flow direction about a rotational axis of the engine. The engine includes a rotor located within the casing and rotatable about the rotational axis, including multiple sets of circumferentially arranged blades, with at least one set corresponding to the compressor section and another set corresponding to the turbine section. The engine also includes a set of vanes circumferentially arranged about the rotational axis and at a location upstream of the combustion section, with the vanes having a pressure side and a suction side. The engine further includes a cooling conduit extending from upstream of the combustion section to downstream of the combustion section, with an inlet located on the suction side of at least one of the vanes which allows cooling air to enter the inlet and is directed through the cooling conduit for cooling.
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公开(公告)号：US20150252683A1
公开(公告)日：2015-09-10
申请号：US13625924
申请日：2012-09-25
Applicant: General Electric Company
Inventor： William Howard Hasting , David William Crall , Craig William Higgins , Erich Alois Krammer
CPC classification number: F01D11/24 , F01D11/20 , F01D25/24 , F02C6/08 , F05D2250/323 , F05D2250/324
Abstract: Active clearance control ejector systems and methods are disclosed. An example system may include an air ejector; an entrance pipe arranged to supply compressor bleed air to the air ejector; an inlet duct arranged to supply fan bypass air to the air ejector; and a supply pipe arranged to receive ejector outlet air from the air ejector and supply the ejector outlet air to an active clearance control system. The ejector outlet air may include a mixture of the compressor bleed air and the fan bypass air. The air ejector may include a venturi arranged to conduct the compressor bleed air therethrough, thereby drawing the fan bypass air into the air ejector.
Abstract translation: 公开了主动间隙控制喷射器系统和方法。 示例性系统可以包括空气喷射器; 入口管，布置成将压缩机排放空气供应到空气喷射器; 入口管道，其布置成将风扇旁路空气供应到空气喷射器; 以及供应管，布置成从喷射器接收喷射器出口空气，并将喷射器出口空气供应到主动间隙控制系统。 喷射器出口空气可以包括压缩机排出空气和风扇旁路空气的混合物。 空气喷射器可以包括文丘里管，其布置成将压缩机排气通过其中，从而将风扇旁路空气抽入空气喷射器。
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公开(公告)号：US20250163850A1
公开(公告)日：2025-05-22
申请号：US18515871
申请日：2023-11-21
Applicant: General Electric Company
Inventor： Arthur W. Sibbach , James R. Reepmeyer , Erich Alois Krammer , Koji Asari , Jeffrey D. Clements
Abstract: A turbine engine for an aircraft includes a turbo-engine with a core air flow path, a fan having a fan shaft coupled to the turbo-engine to rotate the fan shaft, and a steam system. The core air flow path includes a plurality of core air flow path zones. A combustor is positioned in the core air flow path to combust fuel and to generate combustion gases. The steam system extracts water from combustion gases and vaporizes the water to generate steam. The steam system is fluidly coupled to a core air flow path to inject the steam into the core air flow path at a plurality of steam injection zones to add mass flow to the core air. Each steam injection zone of the plurality of steam injection zones corresponds to a core air flow path zone of the plurality of core air flow path zones.
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Patent Agency Ranking
公开(公告)号：US12078107B2
公开(公告)日：2024-09-03
申请号：US18500517
申请日：2023-11-02
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Jeffrey Donald Clements , Jeffrey S. Spruill , Erich Alois Krammer , Matthew Kenneth MacDonald , Scott Alan Schimmels
Abstract: A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000).
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公开(公告)号：US20230407761A1
公开(公告)日：2023-12-21
申请号：US17844940
申请日：2022-06-21
Applicant: General Electric Company
Inventor： Arthur William Sibbach , Brandon Wayne Miller , Erich Alois Krammer , Douglas Scott Jacobs , Joseph Alfred Iannotti
CPC classification number: F01D21/02 , F02C9/28 , F02C9/46 , F05D2270/021 , F05D2270/304 , F05D2270/335
Abstract: A method for providing overspeed protection for a gas turbine engine having an engine shaft includes monitoring, via an overspeed protection system, a torque of the engine shaft. The method also includes determining, via the overspeed protection system, at least one additional condition of the engine shaft. Further, the method includes determining, via the overspeed protection system, an overspeed condition of the gas turbine engine when the torque of the engine shaft drops below a torque threshold and the at least one additional condition of the engine shaft is indicative of the gas turbine engine being in an operational state. Thus, the overspeed condition is indicative of an above normal rotational speed of the engine shaft. In addition, the method includes initiating a shutdown procedure for the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.
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公开(公告)号：US11761344B1
公开(公告)日：2023-09-19
申请号：US17724074
申请日：2022-04-19
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Brian Lewis Devendorf , Jeffrey Douglas Rambo , Brian Gene Brzek , Kevin Edward Hinderliter , Erich Alois Krammer , Arthur William Sibbach
CPC classification number: F01D19/02 , F01D25/10 , F01D25/18 , F05D2260/213 , F05D2260/232 , F05D2260/607 , F05D2260/85 , F05D2260/98
Abstract: A method is provided for operating a thermal management system of a gas turbine engine. The method includes: operating the gas turbine engine to start-up the gas turbine engine; receiving data indicative of a state of a thermal transport bus of the thermal management system using a sensor, the state of the thermal transport bus including a phase of a thermal fluid within the thermal transport bus; and starting a pump of a pump assembly in response to receiving data indicative of the state of the thermal transport bus of the thermal management system, the pump in fluid communication with the thermal transport bus.
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公开(公告)号：US10724437B2
公开(公告)日：2020-07-28
申请号：US15635519
申请日：2017-06-28
Applicant: General Electric Company
Inventor： Satoshi Atsuchi , Byron Andrew Pritchard, Jr. , Corey Bourassa , Erich Alois Krammer
Abstract: A particle separator system for use with a turbomachine is provided. The particle separator system includes a first end, a second end opposite the first end, a main separator body extending between the first and second ends, the main separator body including at least one step configured to cause a fluid flow to turn up to 180 degrees, and at least one transversely oriented cyclone separator disposed within the main separator body and defining at least one of a swirling cylinder, a bent cylinder, and a conical volume.
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公开(公告)号：US10196982B2
公开(公告)日：2019-02-05
申请号：US14932162
申请日：2015-11-04
Applicant: General Electric Company
Inventor： Mehmet Muhittin Dede , Satoshi Atsuchi , Byron Andrew Pritchard , Erich Alois Krammer , Giridhar Jothiprasad , Shourya Prakash Otta , Corey Bourassa
IPC: F02C7/18 , F02C9/18 , F01D9/06 , F02C7/052 , F02C6/08 , F01D5/08 , F01D9/04 , F04D29/54 , F04D29/58 , B01D45/16
Abstract: The invention relates to a gas turbine engine comprising a casing having a compressor section, combustion section and turbine section, axially arranged in a flow direction about a rotational axis of the engine. The engine includes a rotor located within the casing and rotatable about the rotational axis, including multiple sets of circumferentially arranged blades, with at least one set corresponding to the compressor section and another set corresponding to the turbine section. The engine also includes a set of vanes circumferentially arranged about the rotational axis and at a location upstream of the combustion section, with the vanes having a pressure side and a suction side. The engine further includes a cooling conduit extending from upstream of the combustion section to downstream of the combustion section, with an inlet located on the suction side of at least one of the vanes which allows cooling air to enter the inlet and is directed through the cooling conduit for cooling.
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