Patents by Inventor SI-MAN AMY LAO
SI-MAN AMY LAO has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11885497Abstract: A fuel nozzle assembly comprising an annular slot surrounding a fuel nozzle, the annular slot having gas passages for feeding a gas into the slot and against an opposing wall of the slot. A method of operating a gas turbine engine including directing a gas flow into and across the slot against an opposing wall of the slot to generate a circulating gas flow filling the slot, the gas flow passing into the slot through one or more gas outlets within the slot and thereafter said gas flow exiting the slot into the combustion chamber, the gas outlets spaced away from the closed end of the slot. A gas turbine engine comprising a slot formed in a fuel nozzle assembly, the slot having one or more gas passages extending through a wall of the slot and feeding a gas into the slot against a another wall of the slot.Type: GrantFiled: July 19, 2019Date of Patent: January 30, 2024Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Si-Man Amy Lao
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Patent number: 11125436Abstract: A floating collar assembly is configured to receive a fuel nozzle or an igniter projecting through an opening defined in a combustor shell lined with heat shields having studs projecting through the combustor shell for engagement with corresponding fasteners outside the combustor shell. A floating collar is mounted outside the combustor shell with an opening in alignment with the opening in the combustor shell for receiving the fuel nozzle or the igniter. An external retaining bracket is mounted to the heat shield studs or other studs projecting outwardly from the combustor shell so as to trap the floating collar between the combustor shell and the bracket.Type: GrantFiled: July 3, 2019Date of Patent: September 21, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Maximilian Baranowicz, Si-Man Amy Lao, Oleg Morenko
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Patent number: 11085644Abstract: A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.Type: GrantFiled: July 11, 2019Date of Patent: August 10, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael Papple, Si-Man Amy Lao, Sri Sreekanth
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Patent number: 11015807Abstract: A combustor heat shield comprises a panel body having a front surface and a back surface. The back surface has sealing rails extending therefrom and defining a serpentine cooling path on the back surface of the panel body.Type: GrantFiled: January 30, 2019Date of Patent: May 25, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Si-Man Amy Lao
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Publication number: 20210018174Abstract: A fuel nozzle assembly comprising an annular slot surrounding a fuel nozzle, the annular slot having gas passages for feeding a gas into the slot and against an opposing wall of the slot. A method of operating a gas turbine engine including directing a gas flow into and across the slot against an opposing wall of the slot to generate a circulating gas flow filling the slot, the gas flow passing into the slot through one or more gas outlets within the slot and thereafter said gas flow exiting the slot into the combustion chamber, the gas outlets spaced away from the closed end of the slot. A gas turbine engine comprising a slot formed in a fuel nozzle assembly, the slot having one or more gas passages extending through a wall of the slot and feeding a gas into the slot against a another wall of the slot.Type: ApplicationFiled: July 19, 2019Publication date: January 21, 2021Inventor: Si-Man Amy LAO
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Publication number: 20210003283Abstract: A floating collar assembly is configured to receive a fuel nozzle or an igniter projecting through an opening defined in a combustor shell lined with heat shields having studs projecting through the combustor shell for engagement with corresponding fasteners outside the combustor shell. A floating collar is mounted outside the combustor shell with an opening in alignment with the opening in the combustor shell for receiving the fuel nozzle or the igniter. An external retaining bracket is mounted to the heat shield studs or other studs projecting outwardly from the combustor shell so as to trap the floating collar between the combustor shell and the bracket.Type: ApplicationFiled: July 3, 2019Publication date: January 7, 2021Inventors: Maximilian BARANOWICZ, Si-Man Amy LAO, Oleg MORENKO
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Patent number: 10876730Abstract: A gas turbine engine combustor has a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone. The shell has an outer skin and an inner skin defining an air gap therebetween. The inner skin in the upstream portion of the primary zone is free from effusion holes and has heat transfer augmenters projecting from a back side thereof into the air gap. Effusion holes in the inner skin are only disposed downstream towards the tail end of the primary zone in order to delay the injection of any disruptive cooling air that could potentially interfere with the combustion process.Type: GrantFiled: February 25, 2016Date of Patent: December 29, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Hayley Ozem, Si-Man Amy Lao, Sri Sreekanth, Jeffrey Verhiel
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Patent number: 10830436Abstract: A combustor heat shield comprises a panel body having a front surface and a back surface. The back surface has rail-less edges and a turbulator band extending inwardly from the rail-less edges. The band includes a plurality of turbulators defining tortuous cooling paths up to the rail-less edges. Effusion holes are distributed over the central area.Type: GrantFiled: March 20, 2018Date of Patent: November 10, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Si-Man Amy Lao
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Patent number: 10753283Abstract: A combustor heat shield has a heat shield body having a first surface configured to face a combustor shell and an opposed second surface configured to face towards the combustion gases in the combustion chamber. A dilution or igniter hole is defined in the heat shield body. An array of circumferentially spaced-apart cooling holes is provided around the at least one dilution or igniter hole. The cooling holes are oriented to locally deliver a swirl of cooling air around an axis of the dilution or igniter hole. The cooling holes are angled relative to the heat shield body and extend from an inlet on the first surface to an outlet on the second surface. The outlet is positioned closer to a perimeter of the dilution or igniter hole than the inlet.Type: GrantFiled: March 20, 2017Date of Patent: August 25, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Si-Man Amy Lao
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Publication number: 20200240640Abstract: A combustor heat shield comprises a panel body having a front surface and a back surface. The back surface has sealing rails extending therefrom and defining a serpentine cooling path on the back surface of the panel body.Type: ApplicationFiled: January 30, 2019Publication date: July 30, 2020Inventor: Si-Man Amy LAO
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Publication number: 20190353349Abstract: A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.Type: ApplicationFiled: July 11, 2019Publication date: November 21, 2019Inventors: Michael PAPPLE, Si-Man Amy LAO, Sri SREEKANTH
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Publication number: 20190293289Abstract: A combustor heat shield comprises a panel body having a front surface and a back surface. The back surface has rail-less edges and a turbulator band extending inwardly from the rail-less edges. The band includes a plurality of turbulators defining tortuous cooling paths up to the rail-less edges. Effusion holes are distributed over the central area.Type: ApplicationFiled: March 20, 2018Publication date: September 26, 2019Inventor: Si-Man Amy LAO
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Patent number: 10386072Abstract: A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.Type: GrantFiled: September 2, 2015Date of Patent: August 20, 2019Assignee: Pratt & Whitney Canada Corp.Inventors: Michael Papple, Si-Man Amy Lao, Sri Sreekanth
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Patent number: 10260751Abstract: A combustor for a gas turbine engine comprises a single skin liner defining a combustion chamber. The single skin liner has an inner surface facing the combustion chamber and an outer surface exposed to a coolant flow discharged in a plenum extending from the outer surface of the single skin liner to the engine casing. Cooling holes extend through the single skin liner. Cooling protuberances, such as fins or pin fins, project integrally from the outer surface of the single skin liner into the plenum, the cooling fins being interspersed between the cooling holes.Type: GrantFiled: September 28, 2015Date of Patent: April 16, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Tin-Cheung John Hu, Si-Man Amy Lao, Sri Sreekanth, Michael Papple
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Publication number: 20180266324Abstract: A combustor heat shield has a heat shield body having a first surface configured to face a combustor shell and an opposed second surface configured to face towards the combustion gases in the combustion chamber. A dilution or igniter hole is defined in the heat shield body. An array of circumferentially spaced-apart cooling holes is provided around the at least one dilution or igniter hole. The cooling holes are oriented to locally deliver a swirl of cooling air around an axis of the dilution or igniter hole. The cooling holes are angled relative to the heat shield body and extend from an inlet on the first surface to an outlet on the second surface. The outlet is positioned closer to a perimeter of the dilution or igniter hole than the inlet.Type: ApplicationFiled: March 20, 2017Publication date: September 20, 2018Inventor: Si-Man Amy LAO
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Publication number: 20170248311Abstract: A gas turbine engine combustor has a shell defining a combustion chamber having a primary zone and a dilution zone downstream of the primary zone. The shell has an outer skin and an inner skin defining an air gap therebetween. The inner skin in the upstream portion of the primary zone is free from effusion holes and has heat transfer augmenters projecting from a back side thereof into the air gap. Effusion holes in the inner skin are only disposed downstream towards the tail end of the primary zone in order to delay the injection of any disruptive cooling air that could potentially interfere with the combustion process.Type: ApplicationFiled: February 25, 2016Publication date: August 31, 2017Inventors: HAYLEY OZEM, SI-MAN AMY LAO, SRI SREEKANTH, JEFFREY VERHIEL
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Publication number: 20170089580Abstract: A combustor for a gas turbine engine comprises a single skin liner defining a combustion chamber. The single skin liner has an inner surface facing the combustion chamber and an outer surface exposed to a coolant flow discharged in a plenum extending from the outer surface of the single skin liner to the engine casing. Cooling holes extend through the single skin liner. Cooling protuberances, such as fins or pin fins, project integrally from the outer surface of the single skin liner into the plenum, the cooling fins being interspersed between the cooling holes.Type: ApplicationFiled: September 28, 2015Publication date: March 30, 2017Inventors: TIN-CHEUNG JOHN HU, SI-MAN AMY LAO, SRI SREEKANTH, MICHAEL PAPPLE
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Publication number: 20170089581Abstract: A combustor for a gas turbine engine comprises a single skin liner defining a combustion chamber. The single skin liner has an inner surface facing the combustion chamber and an outer surface exposed to a coolant flow discharged in a plenum extending from the outer surface of the single skin liner to the engine casing. Cooling holes extend through the single skin liner. Open flow guiding channels are provided on the outer surface of the single skin liner, the open flow guiding channels being uncovered and aligned with the flow of air over the outer surface of the single skin liner.Type: ApplicationFiled: September 28, 2015Publication date: March 30, 2017Inventors: SI-MAN AMY LAO, SRI SREEKANTH, MICHAEL PAPPLE
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Publication number: 20170059162Abstract: A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.Type: ApplicationFiled: September 2, 2015Publication date: March 2, 2017Inventors: MICHAEL PAPPLE, SI-MAN AMY LAO, SRI SREEKANTH