Patents by Inventor Vincent P. Laurello
Vincent P. Laurello 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: 9562475Abstract: A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of the engine to a first section of a vane carrier that supports a plurality of rows of vanes within a turbine section of the engine. The second cooling air source supplies a second portion of vane carrier cooling air extracted from the compressor section to a second section of the vane carrier spaced from the first section in an axial direction defined by a direction of hot working gas flow through the turbine section. The air temperature control system controls a temperature of at least one of the first and second portions of vane carrier cooling air.Type: GrantFiled: December 19, 2012Date of Patent: February 7, 2017Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Vincent P. Laurello, Kok-Mun Tham
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Patent number: 9494081Abstract: A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing. The upper side region may be positioned above a horizontally extending centerline of the casing. Fluids may be exhausted from one or more exhaust slots in the casing temperature control housing to isolate the upper side region of the casing from buoyancy effects of hot gases within the casing after shutdown of the gas turbine engine.Type: GrantFiled: May 9, 2013Date of Patent: November 15, 2016Assignee: Siemens AktiengesellschaftInventor: Vincent P. Laurello
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Patent number: 9206904Abstract: A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.Type: GrantFiled: July 8, 2010Date of Patent: December 8, 2015Assignee: Siemens Energy, Inc.Inventors: Ching-Pang Lee, Vincent P. Laurello, Chander Prakash, Kok-Mun Tham
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Patent number: 9157331Abstract: The present invention comprises a gas turbine engine with a compressor for generating compressed air, a turbine comprising upstream and downstream rows of vanes, vane carrier structure surrounding at least one row of vanes and plenum structure at least partially surrounding the vane carrier structure capable of impinging compressed air onto the vane carrier structure. The gas turbine engine further comprises fluid supply structure including first fluid path structure defining a first path for compressed air to travel to the plenum structure, second fluid path structure defining a second path for compressed air to travel toward the downstream row of vanes, and fluid control structure selectively controlling fluid flow to the first and second fluid path structures.Type: GrantFiled: December 8, 2011Date of Patent: October 13, 2015Assignee: Siemens AktiengesellschaftInventor: Vincent P. Laurello
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Patent number: 9151175Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting alternating rows of first and second height ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. The first ridges have a first ridge height greater than that of the second ridges. These ridge or rib embodiments have first lower and second upper wear zones. The lower zone, at and below the second ridge height, optimizes engine airflow characteristics, while the upper zone, between tips of the second and first ridges, is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.Type: GrantFiled: February 25, 2014Date of Patent: October 6, 2015Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Kok-Mun Tham, Vincent P. Laurello, Ching-Pang Lee, Gm Salam Azad, Nicholas F. Martin, Jr., David G. Sansom, Neil Hitchman
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Patent number: 9121298Abstract: A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.Type: GrantFiled: June 27, 2012Date of Patent: September 1, 2015Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Ching-Pang Lee, Kok-Mun Tham, John M. Owen, Gary D. Lock, Carl M. Sangan, Vincent P. Laurello
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Publication number: 20150240651Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting alternating rows of first and second height ridges in planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. The first ridges have a first ridge height greater than that of the second ridges. These ridge or rib embodiments have first lower and second upper wear zones. The lower zone, at and below the second ridge height, optimizes engine airflow characteristics, while the upper zone, between tips of the second and first ridges, is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.Type: ApplicationFiled: February 25, 2014Publication date: August 27, 2015Applicant: Siemens AktiengesellschaftInventors: Kok-Mun Tham, Vincent P. Laurello, Ching-Pang Lee, Gm Salam Azad, Nicholas F. Martin, JR., David G. Sansom, Neil Hitchman
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Patent number: 9068461Abstract: A turbine rotor body having at least one inlet orifice in fluid communication with a pre-swirl system such that the inlet orifice receives cooling fluids from the pre-swirl system is disclosed. The inlet orifice may be configured to reduce the relative velocity loss associated with cooling fluids entering the inlet orifice in the rotor, thereby availing the cooling system to the efficiencies inherent in pre-swirling the cooling fluids to a velocity that is greater than a rotational velocity of the turbine rotor body. As such, the system is capable of taking advantage of the additional temperature and work benefits associated with using the pre-swirled cooling fluids having a rotational speed greater than the turbine rotor body.Type: GrantFiled: August 18, 2011Date of Patent: June 30, 2015Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Vincent P. Laurello, Ching-Pang Lee
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Patent number: 9062557Abstract: A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).Type: GrantFiled: September 7, 2011Date of Patent: June 23, 2015Assignee: Siemens AktiengesellschaftInventors: Kok-Mun Tham, Ching-Pang Lee, Abdullatif M. Chehab, Gm Salam Azad, Shantanu P. Mhetras, Manjit Shivanand, Vincent P. Laurello, Christopher Rawlings
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Patent number: 9032738Abstract: A gas turbine engine includes a compressor for generating compressed air. The compressor includes a rotor defined by a plurality of axial disks including a first disk and a second disk. A first row of blades extends radially outwardly from the first disk, and a second row of blades extends radially outwardly from the second disk. A row of cantilevered vanes is located at an axial location between the first row of blades and the second row of blades. A bleed path extends at least partially through the second disk and includes an entrance at an axial location between the first row of blades and at least a portion of the row of cantilevered vanes. The entrance communicates with a compressed air flowpath through the compressor.Type: GrantFiled: April 25, 2012Date of Patent: May 19, 2015Assignee: Siemens AktiengeselischaftInventors: Vincent P. Laurello, Kok-Mun Tham
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Patent number: 9017013Abstract: A gas turbine engine is provided comprising a forward rotor disk and blade assembly capable of rotating; an aft rotor disk and blade assembly capable of rotating; and a row of vanes positioned between the forward rotor disk and blade assembly and the aft rotor disk and blade assembly. The vane row and the forward rotor disk and blade assembly may define a forward cavity. The vane row may comprise at least one stator vane comprising: a main body and an inner shroud structure comprising a cover. The cover may include a first inner cavity receiving cooling air. The cover may further include at least one cooling flow passage. Cooling air flowing from the cooling flow passage has a tangential velocity component.Type: GrantFiled: February 7, 2012Date of Patent: April 28, 2015Assignee: Siemens AktiengesellschaftInventors: Vincent P. Laurello, Kok-Mun Tham
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Patent number: 8939716Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with nested loop pattern abradable surface ridges and grooves. The nested loops comprise nested fully closed loops or a spiraling maze pattern loop. Some embodiments include distinct forward upstream and aft downstream composite multi orientation groove and vertically projecting ridges planform patterns, to reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. Ridge or rib embodiments have first lower and second upper wear zones. The lower zone optimizes engine airflow characteristics while the upper zone is optimized to minimize blade tip gap and wear by being more easily abradable than the lower zone.Type: GrantFiled: February 25, 2014Date of Patent: January 27, 2015Assignee: Siemens AktiengesellschaftInventors: Ching-Pang Lee, Kok-Mun Tham, Vincent P. Laurello, Gm Salam Azad, Nicholas F. Martin, Jr.
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Patent number: 8939711Abstract: A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.Type: GrantFiled: February 15, 2013Date of Patent: January 27, 2015Assignee: Siemens AktiengesellschaftInventors: Ching-Pang Lee, Kok-Mun Tham, Manjit Shivanand, Vincent P. Laurello, Gm Salam Azad, Nicholas F. Martin, Jr.
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Publication number: 20140331637Abstract: A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing. The upper side region may be positioned above a horizontally extending centerline of the casing. Fluids may be exhausted from one or more exhaust slots in the casing temperature control housing to isolate the upper side region of the casing from buoyancy effects of hot gases within the casing after shutdown of the gas turbine engine.Type: ApplicationFiled: May 9, 2013Publication date: November 13, 2014Inventor: VINCENT P. LAURELLO
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Publication number: 20140311157Abstract: A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of the engine to a first section of a vane carrier that supports a plurality of rows of vanes within a turbine section of the engine. The second cooling air source supplies a second portion of vane carrier cooling air extracted from the compressor section to a second section of the vane carrier spaced from the first section in an axial direction defined by a direction of hot working gas flow through the turbine section. The air temperature control system controls a temperature of at least one of the first and second portions of vane carrier cooling air.Type: ApplicationFiled: December 19, 2012Publication date: October 23, 2014Inventors: Vincent P. Laurello, Kok-Mun Tham
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Patent number: 8820091Abstract: A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.Type: GrantFiled: November 7, 2012Date of Patent: September 2, 2014Assignee: Siemens AktiengesellschaftInventors: Kok-Mun Tham, Ching-Pang Lee, Vincent P. Laurello, Abdullatif M. Chehab, David A. Kemp, John A. Fussner, Yan Yin, Bijay K. Sultanian, Weidong Cai
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Publication number: 20140234076Abstract: A seal assembly between a hot gas path and a disc cavity in a turbine engine includes a non-rotatable vane assembly including a row of vanes and an inner shroud, a rotatable blade assembly adjacent to the vane assembly and including a row of blades and a turbine disc that forms a part of a turbine rotor, and an annular wing member located radially between the hot gas path and the disc cavity. The wing member extends generally axially from the blade assembly toward the vane assembly and includes a plurality of circumferentially spaced apart flow passages extending therethrough from a radially inner surface thereof to a radially outer surface thereof. The flow passages effect a pumping of cooling fluid from the disc cavity toward the hot gas path during operation of the engine.Type: ApplicationFiled: February 15, 2013Publication date: August 21, 2014Inventors: Ching-Pang Lee, Kok-Mun Tham, Manjit Shivanand, Vincent P. Laurello, Gm Salam Azad, Nicholas F. Martin, JR.
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Patent number: 8727703Abstract: A gas turbine engine includes a diffuser section supplying cooling fluid, a rotatable shaft, shaft cover structure disposed about the rotatable shaft, support structure, and a cooling fluid channel between the shaft cover structure and the support structure. The support structure provides structural support for the shaft cover structure and receives cooling fluid from the diffuser section. One of the diffuser section and the support structure comprises a plurality of apertures through which at least a portion of the cooling fluid passes. The cooling fluid channel is in fluid communication with the apertures in the one of the diffuser section and the support structure for supplying cooling fluid to a blade disc structure located in a turbine section of the engine.Type: GrantFiled: September 7, 2010Date of Patent: May 20, 2014Assignee: Siemens Energy, Inc.Inventors: Vincent P. Laurello, Keith D. Kimmel, John Orosa
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Publication number: 20140123657Abstract: A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.Type: ApplicationFiled: November 7, 2012Publication date: May 8, 2014Inventors: Kok-Mun Tham, Ching-Pang Lee, Vincent P. Laurello, Abdullatif M. Chehab, David A. Kemp, John A. Fussner, Yan Yin, Bijay K. Sultanian, Weidong Cai
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Patent number: 8677766Abstract: A gas turbine engine comprises a pre-swirl structure coupled to a shaft cover structure and located radially between a supply of cooling fluid and a flow path. The pre-swirl structure defines a flow passage and includes a plurality of swirl members in the flow passage. A flow direction of cooling fluid passing through the flow passage is altered by the swirl members such that the cooling fluid has a velocity component in a direction tangential to the circumferential direction. The bypass passages provide cooling fluid into a turbine rim cavity associated with a first row vane assembly to prevent hot gas ingestion into the turbine rim cavity from a hot gas flow path associated with a turbine section of the engine.Type: GrantFiled: August 20, 2010Date of Patent: March 25, 2014Assignee: Siemens Energy, Inc.Inventors: Vincent P. Laurello, Keith D. Kimmel, Todd Ebert