-
公开(公告)号：US20190186357A1
公开(公告)日：2019-06-20
申请号：US16282891
申请日：2019-02-22
Applicant: United Technologies Corporation
CPC classification number: F02C3/113 , F02C3/06 , F02C7/36 , F02C9/16 , F02K3/06 , F02K3/072 , F05D2200/221 , F05D2220/3215 , F05D2220/323 , F05D2260/40311 , F05D2270/20
Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including fan blades, an outer housing that surrounds the fan to define a bypass flow path, a compressor section in fluid communication with the fan, the compressor section including a low pressure compressor section and a high pressure compressor section, a turbine section including a fan drive turbine section driving the fan and the low pressure compressor section and a high pressure turbine section driving the high pressure compressor section. A gear reduction including an epicyclic gear train is between the fan drive turbine section and the low pressure compressor section such that the low pressure compressor section and the fan are rotatable at a common speed and such that the fan is rotatable at a lower speed than the fan drive turbine section. The fan drive turbine section has a first exit area at a first exit point and is rotatable at a first speed, the high pressure turbine section has a second exit area at a second exit point and is rotatable at a second speed, which is higher than the first speed. A first performance quantity is defined as a product of the first speed squared and the first area, a second performance quantity is defined as a product of the second speed squared and the second exit area and a performance ratio of the first performance quantity to the second performance quantity is between 0.2 and 0.8.
-
公开(公告)号：US10287991B2
公开(公告)日：2019-05-14
申请号：US14600101
申请日：2015-01-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine comprises a gas generator rotating along a first axis of rotation, with at least one compressor rotor, at least one gas generator turbine rotor and a combustion section. A fan drive turbine rotates along a second axis of rotation, downstream of at least one gas generator turbine rotor. The fan drive turbine drives a pair of shaft portions extending in opposed directions beyond the axis of rotation of the gas generator.
-
23.发明授权公开(公告)号：US10287914B2
公开(公告)日：2019-05-14
申请号：US15478706
申请日：2017-04-04
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Gabriel L. Suciu , William K. Ackermann , Daniel Bernard Kupratis , Michael E. McCune
IPC: F01D15/12 , F01D25/16 , F04D25/04 , F04D25/02 , F04D27/00 , F04D29/32 , F04D19/02 , F01D5/06 , F01D9/04 , F02C3/107 , F02C7/36 , F02K3/06 , F02C3/04
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine section including a fan drive turbine and a second turbine. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.
-
公开(公告)号：US10267263B2
公开(公告)日：2019-04-23
申请号：US15230590
申请日：2016-08-08
Applicant: United Technologies Corporation
Inventor： Wesley K. Lord , Jesse M. Chandler , Gabriel L. Suciu
Abstract: A gas turbine engine includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A propulsor section aft of the core engine is driven by the turbine section. An exhaust duct routing exhaust gases around the propulsor section. The exhaust duct includes an inlet forward of the propulsor section, an outlet aft of the turbine section and a passageway between the inlet and the outlet. An aircraft and exhaust duct are also disclosed.
-
公开(公告)号：US10267236B2
公开(公告)日：2019-04-23
申请号：US15137640
申请日：2016-04-25
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler , Kurt J. Sobanski
Abstract: An electromechanical component arrangement for a gas turbine engine includes a mechanical component located at a first side of a firewall of a gas turbine engine and an electronic module of the electromechanical component in communication with the mechanical component separated from the mechanical component by a firewall, the firewall comprising a first side and a second side, the second side having a lower operating temperature than the first side. A vibration isolation structure is located at the second side. The electronic module is connected thereto and includes at least one vibration isolator secured to the firewall to vibrationally isolate the electronic module from gas turbine engine vibrations.
-
Patent Agency Ranking
公开(公告)号：US20190107055A1
公开(公告)日：2019-04-11
申请号：US16158581
申请日：2018-10-12
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , William K. Ackermann
Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.
-
公开(公告)号：US20190107051A1
公开(公告)日：2019-04-11
申请号：US16152502
申请日：2018-10-05
Applicant: United Technologies Corporation
Inventor： Brian D. Merry , Gabriel L. Suciu , Karl L. Hasel
Abstract: A gas turbine engine includes a housing includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. The radially inner boundary of the core inlet is at a location of a core inlet stator and the radially inner boundary of the compressor section inlet is at a location of the first stage low-pressure compressor rotor.
-
公开(公告)号：US10215096B2
公开(公告)日：2019-02-26
申请号：US14932066
申请日：2015-11-04
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A gas turbine engine has a nose cone, a fan for delivering air into a bypass duct as bypass flow, and into a core engine to be delivered to a compressor. The nose cone includes a vent to receive air and deliver the air across a heat exchanger, which receives a fluid to be cooled. The air from the vents is delivered to an outlet downstream of the heat exchanger, such that a majority of the air being delivered to the outlet becomes part of the bypass flow.
-
公开(公告)号：US10202904B2
公开(公告)日：2019-02-12
申请号：US15803418
申请日：2017-11-03
Applicant: United Technologies Corporation
Inventor： Hung Duong , Nathan Snape , Gabriel L. Suciu
IPC: F02C7/36 , F02C7/32 , F02C3/04 , F16H57/025 , F16H57/038 , F01D15/12 , F16H1/22 , F16H57/02
Abstract: A gas turbine engine assembly comprising, a gearbox including a first housing that includes a first auxiliary gear drive on a first portion thereof, a second housing that includes a second auxiliary gear drive on a second portion thereof, and a third housing that includes a third auxiliary gear drive on a third portion thereof, the housings being interconnected so that the first portion of the first housing, the second portion of the second housing and the third portion of the third housing form a substantially triangular polyhedron shape, with the second portion of the second housing disposed between the first portion of the first housing and the third portion of the third housing. The first auxiliary gear drive, the second auxiliary gear drive and the third auxiliary gear drive project outwardly in mutually divergent directions.
-
公开(公告)号：US10161358B2
公开(公告)日：2018-12-25
申请号：US14773958
申请日：2014-03-13
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Jesse M. Chandler
Abstract: A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines.
-
-
-
-
-
-
-
-
-
Search Results
548
records
(took 0.029 seconds)
