-
公开(公告)号：US20230366908A1
公开(公告)日：2023-11-16
申请号：US17987566
申请日：2022-11-15
Applicant: GENERAL ELECTRIC COMPANY POLSKA SP. Z O.O
Inventor： Tomasz Iglewski , Aleksander Piotr Pasieczny
IPC: G01P5/14
Abstract: Methods, apparatus, and articles of manufacture to measure pressure of a fluid are disclosed. An example apparatus to measure a total pressure of a fluid includes a probe head including a plurality of ports, the plurality of ports fluidly coupled to a measurement chamber, and a pressure sensor operatively coupled to the measurement chamber to measure the total pressure inside the measurement chamber, the total pressure corresponding to fluid flow through one of the plurality of ports.
-
公开(公告)号：US11084599B2
公开(公告)日：2021-08-10
申请号：US15869823
申请日：2018-01-12
Applicant: General Electric Company Polska sp. z o.o
Inventor： Tomasz Iglewski , Michal Filipkowski , Aleksander Piotr Pasieczny
Abstract: An apparatus for providing foreign object debris protection an air intake of an aircraft engine. The apparatus includes a frame and a plurality of cross-members. The cross-members are positioned in the frame to define a plurality of screen openings. At least one of the cross-members has an aerodynamically efficient cross section.
-
公开(公告)号：US20250129747A1
公开(公告)日：2025-04-24
申请号：US18592651
申请日：2024-03-01
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Tomasz Iglewski
Abstract: A nacelle for a gas turbine engine includes an interior portion along a radial direction of the gas turbine engine and a heat exchanger. The interior portion defines a heat exchanger duct including an inlet and an outlet. The heat exchanger is disposed in the heat exchanger duct between the inlet and the outlet. The inlet is disposed aft of the outlet along a central axis of the nacelle.
-
公开(公告)号：US12025031B2
公开(公告)日：2024-07-02
申请号：US18081266
申请日：2022-12-14
Applicant: General Electric Company Polska Sp. z o.o.
Inventor： Tomasz Iglewski
IPC: F01D7/00
CPC classification number: F01D7/00 , F05D2220/32 , F05D2220/36
Abstract: A fan assembly is provided for a gas turbine engine including: a plurality of fan blades, the plurality of fan blades including a first fan blade; and an actuation assembly including: a first linkage connected to the first fan blade; a first pivot point rotatable with the first fan blade, the first linkage further connected to the first pivot point; a control point moveable relative to the first pivot point and connected to the first linkage for changing a relative position of the first fan blade within the plurality of fan blades.
-
Patent Agency Ranking
公开(公告)号：US20250129745A1
公开(公告)日：2025-04-24
申请号：US18592663
申请日：2024-03-01
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Tomasz Iglewski
Abstract: A screen for an aeronautical gas turbine engine includes a plurality of first filaments and a plurality of second filaments. The plurality of second filaments define a plurality of openings with the plurality of first filaments. The plurality of first filaments and the plurality of second filaments define a first arrangement in which the plurality of first filaments are perpendicular to the plurality of second filaments. Upon application of a force to the screen, at least some of the plurality of first filaments and at least some of the plurality of second filaments are configured to translate from the first arrangement to a second arrangement in which a size of at least one of the openings is configured to change from a first size to a second size.
-
公开(公告)号：US20230358144A1
公开(公告)日：2023-11-09
申请号：US18081266
申请日：2022-12-14
Applicant: General Electric Company Polska Sp. z o.o.
Inventor： Tomasz Iglewski
IPC: F01D7/00
CPC classification number: F01D7/00 , F05D2220/36 , F05D2220/32
Abstract: A fan assembly is provided for a gas turbine engine including: a plurality of fan blades, the plurality of fan blades including a first fan blade; and an actuation assembly including: a first linkage connected to the first fan blade; a first pivot point rotatable with the first fan blade, the first linkage further connected to the first pivot point; a control point moveable relative to the first pivot point and connected to the first linkage for changing a relative position of the first fan blade within the plurality of fan blades.
-
公开(公告)号：US12276227B1
公开(公告)日：2025-04-15
申请号：US18592663
申请日：2024-03-01
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Tomasz Iglewski
Abstract: A screen for an aeronautical gas turbine engine includes a plurality of first filaments and a plurality of second filaments. The plurality of second filaments define a plurality of openings with the plurality of first filaments. The plurality of first filaments and the plurality of second filaments define a first arrangement in which the plurality of first filaments are perpendicular to the plurality of second filaments. Upon application of a force to the screen, at least some of the plurality of first filaments and at least some of the plurality of second filaments are configured to translate from the first arrangement to a second arrangement in which a size of at least one of the openings is configured to change from a first size to a second size.
-
公开(公告)号：US20220194617A1
公开(公告)日：2022-06-23
申请号：US17381448
申请日：2021-07-21
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Tomasz Iglewski
Abstract: A screen for an air intake portion of a machine is provided. The screen includes an assembly of screen members that form a plurality of screen cells, wherein at least a portion of the screen cells define an irregular configuration.
-
公开(公告)号：US20180363588A1
公开(公告)日：2018-12-20
申请号：US15992416
申请日：2018-05-30
Applicant: General Electric Company Polska Sp. Z o.o.
Inventor： Tomasz Iglewski
Abstract: An apparatus and method for an exhaust assembly for a turbine engine including a reverse flow portion. The exhaust assembly can include an exhaust stub extending between an exhaust collector and an exhaust outlet to define an exhaust conduit having the reverse flow portion. A flow of combustion gases can exit the engine and travel through the exhaust assembly. The exhaust assembly can be applied to a turboprop engine.
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.018 seconds)
