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1 | US10883380B2 |
Airfoil deicing system
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Publication/Patent Number: US10883380B2 | Publication Date: 2021-01-05 | Application Number: 16/111,739 | Filing Date: 2018-08-24 | Inventor： Roberge gary d | Assignee: RAYTHEON TECHNOLOGIES CORPORATION | IPC: F01D25/02 | Abstract: A gas turbine engine includes an airfoil and a deicing system. The airfoil radially extends from a hub towards a case disposed about a central longitudinal axis of the gas turbine engine. The deicing system includes an acoustic driver assembly arranged to apply acoustic energy to the airfoil to excite a predetermined vibratory mode of the airfoil. | |||
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2 | US10612414B2 |
Panel based heat exchanger
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Publication/Patent Number: US10612414B2 | Publication Date: 2020-04-07 | Application Number: 15/243,249 | Filing Date: 2016-08-22 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F28D9/00 | Abstract: A heat exchanger includes a heat exchanger body having a plurality of stacked panels defining an internal manifold and an external manifold. Each of the stacked panels includes an internal structure partially defining an internal manifold, an external structure partially defining the external manifold, and a plurality of ribs connecting the internal structure to the external structure. Each of the ribs further comprises a channel protruding into the rib and being paired with a corresponding rib of an adjacent panel, such that each of the ribs and the corresponding rib defining a cooling passage fluidly connecting the internal manifold to the external manifold. Each of the stacked panels is bonded to at least one adjacent stacked panel. | |||
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3 | US2020088098A1 |
HYBRID EXPANDER CYCLE WITH PRE-COMPRESSION COOLING AND TURBO-GENERATOR
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Publication/Patent Number: US2020088098A1 | Publication Date: 2020-03-19 | Application Number: 16/131,712 | Filing Date: 2018-09-14 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F02C7/143 | Abstract: A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes an air inlet, compressor, combustor, turbine, and heat exchange system. The heat exchange system is configured to transfer thermal energy from an inlet air flow or exhaust air flow to a fuel to produce a gaseous fuel that is used to drive a fuel turbine and fuel pump and used for combustion in the gas turbine engine. The fuel turbine is in fluid communication with the heat exchange system and the combustor and configured to extract energy from expansion of the gaseous fuel. The fuel pump is configured to be driven by the fuel turbine and is in fluid communication with the heat exchanger system. | |||
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4 | US2020173365A1 |
THERMAL MANAGEMENT SYSTEM FOR LOW BYPASS GAS TURBINE ENGINE
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Publication/Patent Number: US2020173365A1 | Publication Date: 2020-06-04 | Application Number: 16/207,806 | Filing Date: 2018-12-03 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F02C7/12 | Abstract: A thermal management system for a gas turbine engine includes an additively manufactured outer engine duct structure, at least a portion of an internal surface of the additively manufactured outer engine duct structure forming an additively manufactured heat exchanger | |||
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5 | EP3623602A1 |
HYBRID EXPANDER CYCLE WITH INTERCOOLING AND TURBO-GENERATOR
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Publication/Patent Number: EP3623602A1 | Publication Date: 2020-03-18 | Application Number: 19197586.1 | Filing Date: 2019-09-16 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F02C3/22 | Abstract: A gas turbine engine system (10, 100, 150) includes a gas turbine engine (12, 112) and a fuel turbine system. The gas turbine engine (12, 112) includes a heat exchange system configured to transfer thermal energy from a first compressed air flow and an exhaust gas flow (FE) to a fuel to produce a gaseous fuel. The fuel turbine system includes a fuel turbine (38) fluidly coupled to the heat exchange system and a combustor (24, 124) of the gas turbine engine (12, 112), and a fuel pump (40) fluidly coupled to the heat exchange system and configured to be driven by the fuel turbine (38). The fuel turbine (38) is configured to extract energy from expansion of the gaseous fuel to produce the gaseous fuel at a lower pressure for delivery to the combustor (24, 124). | |||
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6 | EP3628849A1 |
THRUST BALANCE CONTROL WITH DIFFERENTIAL POWER EXTRACTION
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Publication/Patent Number: EP3628849A1 | Publication Date: 2020-04-01 | Application Number: 19199648.7 | Filing Date: 2019-09-25 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F02C7/32 | Abstract: A gas turbine engine (20) includes a first spool (30) including a first compressor (44) coupled to a first turbine (46) through a first shaft (40); a second spool (32) including a second compressor (52) coupled to a second turbine (54) through a second shaft (50); a first tower shaft (66) coupled to the first shaft (40) through a first gear assembly (100,102); a second tower shaft (70) coupled to the second shaft through a second gear assembly (104,106); and a first load generating device (64) driven by the first tower shaft (66), wherein the first load generating device (64) generates a first load on the first spool (30) through the first tower shaft (66); a second load generating device (68) driven by the second tower shaft (70), wherein the second load generating device (68) generates a second load on the second spool (32) through the second tower shaft (70) and the first load and the second load combine to apply a total load on the first spool (30) and the second spool (32); and a controller (72) controlling each of the first load generating device (64) and the second load generating device (68) to vary a proportion of the total load applied to each of the first spool (30) and the second spool (32) to bias a direction of an axial load on each of the first spool (30) and the second spool (32). | |||
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7 | EP3663562A1 |
THERMAL MANAGEMENT SYSTEM FOR LOW BYPASS GAS TURBINE ENGINE
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Publication/Patent Number: EP3663562A1 | Publication Date: 2020-06-10 | Application Number: 19213167.0 | Filing Date: 2019-12-03 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F02C7/18 | Abstract: A thermal management system (80) for a gas turbine engine (20) includes an additively manufactured outer engine duct structure (42), at least a portion of an internal surface (90) of the additively manufactured outer engine duct structure (42) forming an additively manufactured heat exchanger (82). | |||
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8 | US10801413B2 |
Electromagnetic anti-windmilling system
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Publication/Patent Number: US10801413B2 | Publication Date: 2020-10-13 | Application Number: 15/089,891 | Filing Date: 2016-04-04 | Inventor： Roberge gary d | Assignee: Raytheon Technologies Corporation | IPC: F01D15/10 | Abstract: A gas turbine engine including a compressor has a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine includes a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. The first shaft includes at least one magnetic section. An electromagnet is disposed radially outward of the first shaft at an axial location of the at least one magnetic section, relative to an axis defined by the gas turbine engine. | |||
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9 | US2020362759A1 |
MULTI-MODE HEAT REJECTION SYSTEM
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Publication/Patent Number: US2020362759A1 | Publication Date: 2020-11-19 | Application Number: 16/867,155 | Filing Date: 2020-05-05 | Inventor： Roberge gary d | Assignee: Raytheon Technologies Corporation | IPC: F02C7/18 | Abstract: A turbine engine includes a duct defining an annular passage, at least two heat exchangers arranged within the annular passage and spaced circumferentially apart, a passage between the at least two heat exchangers, and a forward flow control device operable for controlling airflow through the passages. | |||
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10 | US10612462B2 |
Turbomachinery with high relative velocity
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Publication/Patent Number: US10612462B2 | Publication Date: 2020-04-07 | Application Number: 15/103,833 | Filing Date: 2014-12-12 | Inventor： Roberge gary d | Assignee: UNITED TECHNOLOGIES CORPORATION | IPC: F02C1/00 | Abstract: The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a rotating component disposed adjacent to a stationary component. | |||
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11 | US2020047895A1 |
INERTIAL ENERGY STORAGE DEVICE
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Publication/Patent Number: US2020047895A1 | Publication Date: 2020-02-13 | Application Number: 16/057,362 | Filing Date: 2018-08-07 | Inventor： Roberge gary d | Assignee: UNITED TECHNOLOGIES CORPORATION | IPC: B64D27/24 | Abstract: An aircraft power system according to an exemplary embodiment of this disclosure includes, among other possible things, a battery, a motor/generator coupled to the battery, an inertial drum rotatable about an axis of rotation and coupled to the motor/generator, wherein the motor/generator drives rotation of the inertial drum in a first operating mode and is driven by the inertial drum in a second operating mode; and a housing defining a chamber for the inertial drum, the chamber filled with low-viscosity medium to reduce friction on the inertial drum. | |||
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12 | US2020362868A1 |
VARIABLE SPEED BOOST COMPRESSOR FOR GAS TURBINE ENGINE COOLING AIR SUPPLY
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Publication/Patent Number: US2020362868A1 | Publication Date: 2020-11-19 | Application Number: 16/831,955 | Filing Date: 2020-03-27 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F04D25/16 | Abstract: A gas turbine engine has a compressor section with a low pressure compressor and a high pressure compressor having a downstream end. A cooling air system includes a tap from a location upstream of the downstream most location. The tap passes air to a boost compressor, and the boost compressor passes the air back to a location to be cooled. The boost compressor is driven by a shaft in the engine through an epicyclic gear system. A speed control changes the relative speed between an input and an output to the epicyclic gear system. | |||
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13 | EP3623603A1 |
HYBRID EXPANDER CYCLE WITH TURBO-GENERATOR AND COOLED POWER ELECTRONICS
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Publication/Patent Number: EP3623603A1 | Publication Date: 2020-03-18 | Application Number: 19197595.2 | Filing Date: 2019-09-16 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F02C3/22 | Abstract: A gas turbine engine system (10, 50) includes a gas turbine engine (12, 52) and a turbo-generator (14). The gas turbine engine (12, 52) includes a heat exchange system configured to transfer thermal energy from an air flow (i.e., inlet air flow (FI) or exhaust gas flow (FE)) to a fuel to produce a gaseous fuel. The turbo-generator (14) includes a fuel turbine (38) fluidly coupled to the heat exchange system and a combustor (26) of the gas turbine engine (12, 52), a fuel pump (40) configured to be driven by the fuel turbine (38) and fluidly coupled to the heat exchange system, and a motor/generator (42) configured to be driven by the fuel turbine (38). The fuel turbine (38) is configured to extract energy from expansion of the gaseous fuel to produce a gaseous fuel for combustion in the combustor (26). The motor/generator (42) includes a cooling jacket (44), which is fluidly coupled to the fuel pump (40). | |||
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14 | US10814445B2 |
Airfoil machining
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Publication/Patent Number: US10814445B2 | Publication Date: 2020-10-27 | Application Number: 15/149,543 | Filing Date: 2016-05-09 | Inventor： Roberge gary d | Assignee: Raytheon Technologies Corporation | IPC: B23Q3/08 | Abstract: Disclosed is a method for machining a component, comprising: installing the component on a fixture, causing a medium of the fixture to solidify to encase a first portion of the component, applying a toolset to a second portion of the component that is outside of the solidified medium, and subsequent to applying the toolset, extracting the component from the fixture when the medium is in one of a liquid state or a semi-liquid state, where the medium has a melting-point temperature that is less than 500 degrees Fahrenheit. Disclosed is a fixture for machining a component, comprising: a medium configured to encase a first portion of the component when the medium is in a solidified state, and a toolset configured to be applied to a second portion of the component that is outside of the solidified medium, the medium having a melting-point temperature that is less than 500 degrees Fahrenheit. | |||
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15 | US2020300714A1 |
THERMOCHROMATIC TEST DEVICE FOR GAS TURBINE ENGINE
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Publication/Patent Number: US2020300714A1 | Publication Date: 2020-09-24 | Application Number: 16/355,959 | Filing Date: 2019-03-18 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: G01K11/12 | Abstract: A gas turbine engine includes a joint and a flexible strip wrapped circumferentially around the joint. The flexible strip includes a lock operable to fasten the flexible strip about the joint. A thermochromatic layer is attached to a surface of the flexible strip and is operable to change color responsive to a change in temperature. | |||
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16 | US2020378307A1 |
THERMAL MANAGEMENT OF A SHAFT
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Publication/Patent Number: US2020378307A1 | Publication Date: 2020-12-03 | Application Number: 16/426,260 | Filing Date: 2019-05-30 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F02C7/18 | Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section where the turbine section is downstream of the combustor section. A shaft connects the turbine section to the compressor section. A bore tube is disposed within the shaft downstream of the compressor section. The bore tube includes an inlet connected to an air source for passing cooling air in an upstream direction of the shaft. | |||
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17 | EP3231599B1 |
LIGHT WEIGHT HOUSING FOR INTERNAL COMPONENT WITH INTEGRATED THERMAL MANAGEMENT FEATURES AND METHOD OF MAKING
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Publication/Patent Number: EP3231599B1 | Publication Date: 2020-09-09 | Application Number: 17166349.5 | Filing Date: 2017-04-12 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: B32B15/01 | ||||
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18 | US2020088102A1 |
HYBRID EXPANDER CYCLE WITH INTERCOOLING AND TURBO-GENERATOR
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Publication/Patent Number: US2020088102A1 | Publication Date: 2020-03-19 | Application Number: 16/131,706 | Filing Date: 2018-09-14 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F02C7/224 | Abstract: A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from a first compressed air flow and an exhaust gas flow to a fuel to produce a gaseous fuel. The fuel turbine system includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, and a fuel pump fluidly coupled to the heat exchange system and configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce the gaseous fuel at a lower pressure for delivery to the combustor. | |||
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19 | EP2954167B1 |
GAS TURBINE ENGINE FAN SECTION WITH A REMOVABLE FILM MATERIAL AND CORRESPONDING METHOD OF PROTECTING SURFACES IN A FAN SECTION
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Publication/Patent Number: EP2954167B1 | Publication Date: 2020-05-06 | Application Number: 14749072.6 | Filing Date: 2014-02-04 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: F01D5/14 | ||||
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20 | EP3231600B1 |
LIGHT WEIGHT COMPONENT WITH INTERNAL REINFORCEMENT AND METHOD OF MAKING
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Publication/Patent Number: EP3231600B1 | Publication Date: 2020-05-27 | Application Number: 17166353.7 | Filing Date: 2017-04-12 | Inventor： Roberge gary d | Assignee: United Technologies Corporation | IPC: B22F3/26 |
3.Current Quota