-
公开(公告)号：US10677264B2
公开(公告)日：2020-06-09
申请号：US15293368
申请日：2016-10-14
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Daniel Robert Dwyer , Mark John Laricchiuta , Jeffrey Donald Clements , Brandon Wayne Miller
Abstract: A gas turbine engine includes a fan section having a single-stage fan, a core turbine engine, and a nacelle at least partially surrounding the fan of the fan section and the core turbine engine. The gas turbine engine also includes an outlet guide vane extending between a casing of the core turbine engine and the nacelle. The gas turbine engine is configured to define an acoustic ratio greater than or equal to 2.3, with the acoustic ratio being a ratio of an axial spacing between the trailing edge of the fan blade and the leading edge of the outlet guide vane at a radial location seventy-five percent (75%) along the span of the fan blade to the axial width of the fan blade also at the radial location seventy-five percent (75%) along the span of the fan blade.
-
公开(公告)号：US20230035756A1
公开(公告)日：2023-02-02
申请号：US17386065
申请日：2021-07-27
Applicant: General Electric Company
Inventor： Mustafa Dindar , Bernard James Renggli , Andrew J. Hank , Daniel Robert Dwyer , Jeffrey S. Spruill
Abstract: A variable area exhaust nozzle defining an actual area ratio for a gas turbine engine that includes a shroud assembly having a fixed shroud and an adjustable cowl, an adjustable plug, a nozzle adjustment assembly, and a controller configured to receive data indicative of an operating speed of the gas turbine engine; determine a target area ratio based at least in part on received data indicative of the operating speed of the gas turbine engine; and operate the nozzle adjustment assembly to selectively adjust at least one of the adjustable cowl or the adjustable plug such that the actual area ratio is substantially equivalent to the target area ratio.
-
Patent Agency Ranking
公开(公告)号：US20180216576A1
公开(公告)日：2018-08-02
申请号：US15293358
申请日：2016-10-14
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Mark John Laricchiuta , Daniel Robert Dwyer , Jeffrey Donald Clements , Kenneth Scheffel , Thomas Ory Moniz
CPC classification number: F02K3/075 , B64D29/00 , F02K3/06 , F05D2220/80 , F05D2260/96
Abstract: A supersonic turbofan engine includes a fan section having a single-stage fan defining a fan pressure ratio greater than 1.9. The supersonic turbofan engine also includes a core turbine engine defining a core air flowpath. A nacelle at least partially surrounds the fan of the fan section and the core turbine engine. The supersonic turbofan engine defines a bypass ratio, the bypass ratio being greater than or equal to three.
-
公开(公告)号：US11732673B2
公开(公告)日：2023-08-22
申请号：US17386065
申请日：2021-07-27
Applicant: General Electric Company
Inventor： Mustafa Dindar , Bernard James Renggli , Andrew J. Hank , Daniel Robert Dwyer , Jeffrey S. Spruill
CPC classification number: F02K1/09 , B64D33/04 , F02K1/08 , F02K1/18 , F05D2220/323 , F05D2240/1281 , F05D2250/34
Abstract: A variable area exhaust nozzle defining an actual area ratio for a gas turbine engine that includes a shroud assembly having a fixed shroud and an adjustable cowl, an adjustable plug, a nozzle adjustment assembly, and a controller configured to receive data indicative of an operating speed of the gas turbine engine; determine a target area ratio based at least in part on received data indicative of the operating speed of the gas turbine engine; and operate the nozzle adjustment assembly to selectively adjust at least one of the adjustable cowl or the adjustable plug such that the actual area ratio is substantially equivalent to the target area ratio.
-
公开(公告)号：US10550724B2
公开(公告)日：2020-02-04
申请号：US15290132
申请日：2016-10-11
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Daniel Robert Dwyer , Mark John Laricchiuta , Jeffrey Donald Clements , Brandon Wayne Miller
Abstract: A gas turbine engine includes a fan section and a core turbine engine operable with the fan section. The gas turbine engine also includes a sump pressurization assembly including a valve, a first duct in airflow communication with the valve and a first pressurized air source, and a second duct in airflow communication with the valve and a second pressurized air source. Further, the sump pressurization assembly includes a supply duct selectively in airflow communication with the first duct and the second duct through the valve. The supply duct is located at least partially inward of a core air flowpath of the core turbine engine for pressurizing a sump of the gas turbine engine.
-
公开(公告)号：US20180106274A1
公开(公告)日：2018-04-19
申请号：US15293368
申请日：2016-10-14
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Daniel Robert Dwyer , Mark John Laricchiuta , Jeffrey Donald Clements , Brandon Wayne Miller
Abstract: A gas turbine engine includes a fan section having a single-stage fan, a core turbine engine, and a nacelle at least partially surrounding the fan of the fan section and the core turbine engine. The gas turbine engine also includes an outlet guide vane extending between a casing of the core turbine engine and the nacelle. The gas turbine engine is configured to define an acoustic ratio greater than or equal to 2.3, with the acoustic ratio being a ratio of an axial spacing between the trailing edge of the fan blade and the leading edge of the outlet guide vane at a radial location seventy-five percent (75%) along the span of the fan blade to the axial width of the fan blade also at the radial location seventy-five percent (75%) along the span of the fan blade.
-
公开(公告)号：US20180100410A1
公开(公告)日：2018-04-12
申请号：US15290132
申请日：2016-10-11
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Daniel Robert Dwyer , Mark John Laricchiuta , Jeffrey Donald Clements , Brandon Wayne Miller
Abstract: A gas turbine engine includes a fan section and a core turbine engine operable with the fan section. The gas turbine engine also includes a sump pressurization assembly including a valve, a first duct in airflow communication with the valve and a first pressurized air source, and a second duct in airflow communication with the valve and a second pressurized air source. Further, the sump pressurization assembly includes a supply duct selectively in airflow communication with the first duct and the second duct through the valve. The supply duct is located at least partially inward of a core air flowpath of the core turbine engine for pressurizing a sump of the gas turbine engine.
-
-
-
-
-
-
Search Results
7
records
(took 0.018 seconds)
