-
公开(公告)号：US11466579B2
公开(公告)日：2022-10-11
申请号：US16775653
申请日：2020-01-29
Applicant: General Electric Company
Inventor： Victor Hugo Silva Correia , Robert Francis Manning , George Joe-Kueng Chan , James Earl Kopriva
Abstract: The disclosure relates to a gas turbine engine and a method of controlling an upstream extent of a bow wave from an airfoil having a pressure side and a suction side in the turbine engine. In one aspect, the method includes forming a vortex at a leading edge of the airfoil.
-
公开(公告)号：US20220220855A1
公开(公告)日：2022-07-14
申请号：US17148156
申请日：2021-01-13
Applicant: General Electric Company
Inventor： Michael Elia Hayek , Victor Hugo Silva Correia
Abstract: An airfoil for a gas turbine engine defining a radial direction and an axial direction, the airfoil including: a flared portion extending from a suction surface of the airfoil at an outer edge of the airfoil along the radial direction; and a plenum disposed at the outer edge of the airfoil, the plenum having a suction-side sidewall and a pressure-side sidewall, wherein the suction-side sidewall has a first sidewall portion adjacent to a second sidewall portion disposed outside of the first sidewall portion along the radial direction, wherein the first sidewall portion defines a first angle, wherein the second sidewall portion defines a second angle, and wherein the first angle is greater than the second angle.
-
公开(公告)号：US10975731B2
公开(公告)日：2021-04-13
申请号：US15314341
申请日：2015-05-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Robert Francis Manning , Timothy Deryck Stone , Jared Peter Buhler , Victor Hugo Silva Correia , Gregory Michael Laskowski , Robert Carl Murray , Jonathan Russell Ratzlaff , Robert Proctor , John Howard Starkweather , Curtis Walton Stover
IPC: B01D45/16 , F02C7/05 , F02C7/052 , F01D25/32 , B04C3/06 , B04C3/00 , B64D33/08 , F01D5/08 , F01D25/12 , F02C3/04 , F02C7/18 , F02C9/18 , B64D33/02
Abstract: A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.
-
公开(公告)号：US10267179B2
公开(公告)日：2019-04-23
申请号：US14954240
申请日：2015-11-30
Applicant: General Electric Company
Abstract: A centrifugal compressor apparatus includes: an impeller mounted for rotation about a central longitudinal axis, the impeller including an impeller disk carrying an array of impeller blades around its periphery; a diffuser disposed downstream of the impeller, configured to diffuse and turn airflow discharged from the impeller; an extraction scoop disposed in fluid communication with the impeller and with a plenum disposed adjacent the impeller, and a dirt collector disposed in fluid communication with the plenum and configured to trap dirt therein.
-
公开(公告)号：US10227876B2
公开(公告)日：2019-03-12
申请号：US14960991
申请日：2015-12-07
Applicant: General Electric Company
Inventor： Jared Peter Buhler , Ronald Scott Bunker , Victor Hugo Silva Correia , Brian Kenneth Corsetti
Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.
-
Patent Agency Ranking
公开(公告)号：US10221693B2
公开(公告)日：2019-03-05
申请号：US14901450
申请日：2014-07-03
Applicant: General Electric Company
Inventor： George Joe-Kueng Chan , Ronald Scott Bunker , Victor Hugo Silva Correia , Christopher Kanoa Hoffman
Abstract: An airfoil comprises at least one wall defining a leading edge, a trailing edge, a pressure side extending between the leading edge and the trailing edge, and a suction side extending between the leading edge and the trailing edge. The airfoil is curved in three dimensions and has one or more cavities defined by an interior surface of the at least one wall. A plurality of cooling film holes extending between the cavity and at least one cooling trench located on at least one of the pressure side and the suction side, spaced from the leading edge. The at least one trench has a floor spaced from an outer surface of the airfoil. The plurality of cooling film holes extend through the floor at an angle other than perpendicular.
-
公开(公告)号：US20190063232A1
公开(公告)日：2019-02-28
申请号：US15683332
申请日：2017-08-22
Applicant: General Electric Company
Abstract: A turbomachinery component with a surface that includes a bounded wear coat, the component includes: a body; a contact surface defined by the body; a recess extending into the body and communicating with the contact surface; and a wear coat positioned in the recess.
-
公开(公告)号：US10030538B2
公开(公告)日：2018-07-24
申请号：US14933025
申请日：2015-11-05
Applicant: General Electric Company
Inventor： Wilhelm Ramon Hernandez , Daniel Edward Demers , Tyler Frederick Hooper , Victor Hugo Silva Correia , Troy Todd Dennis
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.
-
公开(公告)号：US20180100433A1
公开(公告)日：2018-04-12
申请号：US15287853
申请日：2016-10-07
Applicant: General Electric Company
Inventor： Victor Hugo Silva Correia
CPC classification number: F02C3/14 , F01D9/023 , F01D9/04 , F02C7/28 , F05D2220/3212 , F05D2260/941 , F23R3/002 , F23R3/007 , F23R3/16 , F23R2900/00018 , Y02T50/672 , Y02T50/675
Abstract: A component assembly for a gas turbine engine having a combustor and defining a core air flowpath includes a first wall and a second wall. The first wall is configured for at least partially defining the core air flowpath at a location downstream of a combustion chamber defined by the combustor of the gas turbine engine. Additionally, the second wall is also configured for at least partially defining the core air flowpath at a location downstream of the combustion chamber, and is located opposite the core air flowpath of the first wall. The second wall includes a plurality of fins extending towards the first wall along the radial direction and spaced along the circumferential direction.
-
公开(公告)号：US20130309079A1
公开(公告)日：2013-11-21
申请号：US13662284
申请日：2012-10-26
Applicant: General Electric Company
IPC: F01D25/00
CPC classification number: F01D9/041 , F01D5/189 , F01D25/00 , F05B2230/237 , F05D2240/81 , F05D2260/201 , Y02T50/676
Abstract: A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.
Abstract translation: 涡轮喷嘴段包括：弓形外带段; 所述翼型涡轮叶片从所述外带段径向向内延伸，所述涡轮叶片具有中空的内部; 冲击挡板组件，其固定到所述外部带，以便与所述外部带段协调地限定冲击腔，其中所述冲击挡板组件具有形成在其中的至少一个冲击孔，所述至少一个冲击孔被布置成在所述外部带段处引导冷却空气; 并且至少一个冲击插入件具有形成在其中的至少一个冲击孔，其设置在涡轮叶片的内部，冲击插入件与冲击挡板组件中的开口相配合，使得冲击挡板与冲击腔直接流体连通隔离 。
-
-
-
-
-
-
-
-
-
Search Results
61
records
(took 0.02 seconds)
