General Electric Company

Exxonmobil Upstream Research Company

Carlos Miguel Miranda

Benjamin Paul Lacy

Srikanth Chandrudu Kottilingam

Stanley Kevin Widener

Slawomir Rubinsztajn

Larry Neil Lewis

Gary Michael Itzel

David Edward Schick

Pramod Kumar Biyani

Andrew Lee Trimmer

Gary Charles Liotta

Stanley Frank Simpson

Douglas Frank Beadie

Nilesh Tralshawala

Edward William Cummings

Kenneth Dale Moore

Scott Walter Leyers

Pramod K Biyani

A passive flow modulation device according to an embodiment includes: a pressure sensitive main valve controlling a flow of a cooling fluid from a first area to a second area through an orifice; and a temperature sensitive pilot valve coupled to the pressure sensitive main valve, the temperature sensitive pilot valve configured to open at a predetermined temperature in the first area, causing a pressurization of the pressure sensitive main valve, wherein the pressurization of the pressure sensitive main valve actuates the pressure sensitive main valve to an open position, allowing the cooling fluid to flow from the first area to the second area through the orifice.

Passive flow modulation of cooling flow into a cavity

A bypass valve for a combustor, including: a housing; an opening in the housing; a pneumatically actuated component within the housing; a passage coupling the opening in the housing and a duct of the combustor; a chamber formed by the housing and the pneumatically actuated component, the chamber containing a volume of air; and a control valve for controlling a pressure within the chamber to selectively displace the pneumatically actuated component to open and close the passage.

Pneumatically-actuated bypass valve

An auto thermal valve (ATV) for dual mode passive cooling flow modulation according to an embodiment includes: a gas flow inlet port; a gas flow outlet port; a temperature dependent expandable element; a rod coupled to the temperature expandable element; and a valve disc coupled to a distal end of the rod, the temperature dependent expandable element displacing the valve disc in response to a change in temperature; wherein the valve disc is displaced away from a valve seat by the temperature dependent expandable element at temperatures above and below a range of temperatures to allow a flow of cooling gas to pass from the gas flow inlet port to the gas flow outlet port.

Auto thermal valve (ATV) for dual mode passive cooling flow modulation

A combustor for a gas turbine, including: a combustor chamber; a casing enclosing the combustor chamber and defining an area therebetween for passing compressor discharge air into the combustor chamber for use in combustion; and at least one passive bypass valve for selectively extracting a portion of the compressor discharge air from the area between the combustor chamber and the casing to adjust a temperature in the combustor.

Combustion bypass passive valve system for a gas turbine

A system according to various embodiments includes: a cooling network within a turbine component, the cooling network including at least one passageway fluidly connected with a surface of the turbine component; a cooling fluid source for providing a cooling fluid to the cooling network; and a temperature-actuated flow modulating device fluidly connected with the cooling fluid source and the cooling network, the temperature-actuated flow modulating device configured to: detect an ambient air temperature proximate the turbine component; and control a flow of the cooling fluid to the cooling network based upon the detected ambient air temperature.

Turbine component surface cooling system with passive flow modulation

A turbomachine includes a compressor portion, and a turbine portion operatively connected to the compressor portion. The turbine portion includes a turbine casing. A combustor assembly, including at least one combustor, fluidically connects the compressor portion and the turbine portion. At least one of the compressor portion, turbine portion and combustor assembly includes a sensing cavity. A passive clearance control system is operatively arranged in the turbomachine. The passive clearance control system includes at least one passive flow modulating device mounted in the sensing cavity, and at least one cooling channel extending from the sensing cavity through the casing. The at least one passive flow modulating device selectively passes the fluid from the sensing cavity through the at least one cooling channel to adjust a clearance between stators and rotating airfoils in the turbine portion.

Passive clearance control system for gas turbomachine

A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines an interior space. The outer surface defines a pressure side surface and a suction side surface. The pressure and suction side surfaces are joined together at a leading edge and at a trailing edge. A first cooling passage is formed in the suction side surface of the substrate. It is coupled in flow communication to the interior space. A second cooling passage, separate from the first cooling passage, is formed in the pressure side surface. The second cooling passage is coupled in flow communication to the interior space. A cover is disposed over at least a portion of the first and second cooling passages. The interior space channels a cooling fluid to the first and second cooling passages, which channel the cooling fluid therethrough to remove heat from the component.

Hot gas path component trailing edge having near wall cooling features

A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface of the substrate defines at least one interior space. At least a portion of the outer surface of the substrate includes a recess formed therein. The recess includes a bottom surface and a groove extending at least partially along the bottom surface of the recess. A cover is disposed within the recess and covers at least a portion of the groove. The groove is configured to channel a cooling fluid therethrough to cool the cover.

Hot gas path component having cast-in features for near wall cooling

A cooling system for a hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines at least one interior space. A passage is formed in the substrate between the outer surface and the inner surface. An access passage is formed in the substrate and extends from the outer surface to the inner space. The access passage is formed at a first acute angle to the passage and includes a particle collection chamber. The access passage is configured to channel a cooling fluid to the passage. Furthermore, the passage is configured to channel the cooling fluid therethrough to cool the substrate.

Hot gas path component cooling system having a particle collection chamber

A method for providing micro-channels in a hot gas path component includes forming a first micro-channel in an exterior surface of a substrate of the hot gas path component. A second micro-channel is formed in the exterior surface of the hot gas path component such that it is separated from the first micro-channel by a surface gap having a first width. The method also includes disposing a braze sheet onto the exterior surface of the hot gas path component such that the braze sheet covers at least of portion of the first and second micro-channels, and heating the braze sheet to bond it to at least a portion of the exterior surface of the hot gas path component.

Hot gas path component having near wall cooling features

A component for a turbine engine includes a substrate that includes a first surface, and an insert coupled to the substrate proximate the substrate first surface. The component also includes a channel. The channel is defined by a first channel wall formed in the substrate and a second channel wall formed by at least one coating disposed on the substrate first surface. The component further includes an inlet opening defined in flow communication with the channel. The inlet opening is defined by a first inlet wall formed in the substrate and a second inlet wall defined by the insert.

Turbine component having surface cooling channels and method of forming same

A thermal actuator is provided and includes an expansion material disposed and configured to move a movable element from a first movable element position toward a second movable element position in accordance with an expansion condition of the expansion material. The expansion material includes an inorganic salt mixture or a metal oxide mixture.

Thermal actuator including fluid with high temperature stability

A system includes a gas turbine engine that includes a combustor section having one or more combustors configured to generate combustion products, a turbine section having one or more turbine stages between an upstream end and a downstream end, an exhaust section disposed downstream from the downstream end of the turbine section, and a fluid supply system coupled to the exhaust section. The one or more turbine stages are driven by the combustion products. The exhaust section has an exhaust passage configured to receive the combustion products as an exhaust gas. The fluid supply system is configured to route a cooling gas to the exhaust section. The cooling gas has a temperature lower than the exhaust gas. The cooling gas includes an extracted exhaust gas, a gas separated from the extracted exhaust gas, carbon dioxide, carbon monoxide, nitrogen oxides, or a combination thereof.

System and method for protecting components in a gas turbine engine with exhaust gas recirculation

A thermally actuated assembly for a gas turbine assembly for a gas turbine system includes a heat transfer component having a first portion and a second portion, wherein the first portion is disposed within a first cavity having a first temperature and the second portion is disposed in a second cavity having a second temperature, wherein the heat transfer component extends through a cavity wall, wherein the first temperature is greater than the second temperature. Also included is a temperature sensitive element disposed within the second cavity and in operable communication with the heat transfer component. Further included is a flow manipulating device disposed within the second cavity and configured to displace in response to a temperature change in the first cavity.

Thermally actuated assembly for a gas turbine system and method of controlling a cooling airflow path

A pressure and temperature actuation system is provided having a high-temperature low-pressure zone, a low-temperature high-pressure zone, a boundary, a pressure actuated mechanism, and a temperature mechanism. A gas located in the high-temperature low-pressure zone has a greater gas temperature than the gas located in the low-temperature high-pressure zone. The gas located in the low-temperature high-pressure zone has a greater gas pressure than the gas located in the high-temperature low-pressure zone. The boundary separates the high-temperature low-pressure zone from the low-temperature high pressure zone. The pressure actuated mechanism is located within the boundary and is configured for opening at a specified gas pressure in either the high-temperature low-pressure zone or the low-temperature high-pressure zone. The temperature actuated mechanism is located within the boundary and is configured for opening at a specified gas temperature in either the high-temperature low-pressure zone or the low-temperature high-pressure zone.

Growing community of inventors

Greer, SC, United States of America

Carlos Miguel Miranda