-
公开(公告)号：US11578668B2
公开(公告)日：2023-02-14
申请号：US15608293
申请日：2017-05-30
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , Taryn Narrow , John H. Mosley , Zachary Mott , Paul R. Hanrahan
Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.
-
公开(公告)号：US11268444B2
公开(公告)日：2022-03-08
申请号：US15599149
申请日：2017-05-18
Applicant: United Technologies Corporation
Inventor： Paul R. Hanrahan , Jonathan Ortiz
Abstract: A cooling system for a component of a gas turbine engine includes a first airflow passage configured to direct a first airflow to a mixing chamber and a second airflow passage to configured direct a second airflow to the mixing chamber, the second airflow having a higher temperature than the first airflow, and a cooling airflow passage to direct a cooling airflow from the mixing chamber to the component, the cooling airflow comprising the first airflow and the second airflow. The airflow passages are configured and sized to allow an amount of cooling airflow for unrestricted engine operation. When the first airflow passage is disabled, the second airflow passage and cooling airflow passage are configured and sized to allow an amount of cooling airflow which is adequate to permit continued safe engine operation restricted to within only a portion of its normal parameters and operating envelope.
-
公开(公告)号：US10731500B2
公开(公告)日：2020-08-04
申请号：US15405957
申请日：2017-01-13
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Ortiz
Abstract: A clearance control system for a gas turbine engine comprises a blade outer air seal mounted on a carrier. At least one blade is rotatable about an engine axis. The blade outer air seal is spaced radially outwardly from a tip of the blade by a clearance. A heat exchanger is configured to deliver air at a first temperature to the blade outer air seal at a first operating condition to allow the blade outer air seal to move in a first direction to maintain a desired clearance, and configured to deliver air at a second temperature to the blade outer air seal at a second operating condition to allow the blade outer air seal to move in a second direction to maintain a desired clearance, and wherein the second temperature is less than the first temperature. A gas turbine engine and a method of controlling tip clearance in a gas turbine engine are also disclosed.
-
公开(公告)号：US10718213B2
公开(公告)日：2020-07-21
申请号：US15483752
申请日：2017-04-10
Applicant: United Technologies Corporation
Inventor： Matthew A Devore , Jonathan Ortiz
Abstract: An airfoil may comprise a root and an airfoil body radially outward of the root. The airfoil body may define a first cooling chamber and a second cooling chamber. A first passage may be defined within the root and configured to direct a first airflow radially outward through the root into the first cooling chamber. A second passage may be defined within the root and configured to direct a second airflow radially outward through the root and into the second cooling chamber.
-
公开(公告)号：US20180347472A1
公开(公告)日：2018-12-06
申请号：US15608293
申请日：2017-05-30
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , Taryn Narrow , John H. Mosley , Zachary Mott , Paul R. Hanrahan
Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.
-
Patent Agency Ranking
公开(公告)号：US20180334965A1
公开(公告)日：2018-11-22
申请号：US15601524
申请日：2017-05-22
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , Matthew P. Forcier , William K. Ackermann
CPC classification number: F02C9/18 , F01D9/065 , F01D17/02 , F02C7/18 , F05D2220/32 , F05D2260/20 , F05D2270/30
Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed ports located at one or more axial locations of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. One or more safety sensors are configured to sense operational characteristics of the gas turbine engine, and a controller is operably connected to the one or more safety sensors and configured to evaluate the sensed operational characteristics for anomalies in operation of the bleed air cooling system.
-
公开(公告)号：US20180298770A1
公开(公告)日：2018-10-18
申请号：US15490299
申请日：2017-04-18
Applicant: United Technologies Corporation
Inventor： Matthew A. Devore , Jonathan Ortiz
Abstract: Turbines comprising a first stator section having a plurality of first vanes, a first rotating section having a plurality of first blades, a second stator section having a plurality of second vanes, a “primary TOBI assembly” having an “aft-facing, forward-positioned TOBI” configured to direct an airflow from the first stator section in an aftward direction toward the first rotating section, the primary TOBI assembly supplying high pressure cooling flow to leading edges of the first blades of the first rotating section, and a “secondary TOBI assembly” having a “forward-facing, aft-positioned TOBI” configured to direct an airflow from the second stator section in a forward direction toward the first rotating section, the secondary TOBI assembly supplying low pressure cooling flow to non-leading edge portions of the first blades of the first rotating section.
-
公开(公告)号：US20180291760A1
公开(公告)日：2018-10-11
申请号：US15484166
申请日：2017-04-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Ortiz , Matthew A. Devore , Lane Mikal Thornton , James D. Hill
Abstract: A gas turbine engine comprises a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface defining a diffuser chamber radially outwardly of the combustor, and a cooling air chamber wall positioned outwardly of the diffuser chamber and the combustor, and radially inwardly of a second wall to define a cooling air chamber. The turbine section includes a high pressure turbine first stage blade having an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap taps air having been compressed by the compressor and is passed through a heat exchanger. Air downstream of the heat exchanger passes into the cooling chamber, and then to the blade outer air seal.
-
公开(公告)号：US20200182060A1
公开(公告)日：2020-06-11
申请号：US16794900
申请日：2020-02-19
Applicant: United Technologies Corporation
Inventor： Matthew A. Devore , Jonathan Ortiz
Abstract: An airfoil may comprise a root and an airfoil body radially outward of the root. The airfoil body may define a first cooling chamber and a second cooling chamber. A first passage may be defined within the root and configured to direct a first airflow radially outward through the root into the first cooling chamber. A second passage may be defined within the root and configured to direct a second airflow radially outward through the root and into the second cooling chamber. A tangential onboard injector (TOBI) may be disposed in the first airflow path. A radial onboard injector (ROBI) may be disposed in the second airflow path.
-
公开(公告)号：US10473037B2
公开(公告)日：2019-11-12
申请号：US15601563
申请日：2017-05-22
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , William K. Ackermann , Matthew P. Forcier
Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, a bleed duct configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet, and a delta-pressure valve located at each bleed port of the two or more bleed ports configured to move between an opened position and a closed position in response to a difference between a first pressure upstream of the delta-pressure valve and a second pressure downstream of the delta pressure valve. The bleed airflow is selectably conveyed through a bleed port of the two or more bleed ports depending on the operation of the associated delta-pressure valve.
-
-
-
-
-
-
-
-
-
Search Results
27
records
(took 0.016 seconds)
