Patents by Inventor Matthew D. Montgomery
Matthew D. Montgomery 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: 11306594Abstract: Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: February 25, 2021Date of Patent: April 19, 2022Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.Inventors: Matthew D. Montgomery, William Brian Diggs, Jaewook Song, Jerry W. Wood, John Orosa
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Patent number: 11293286Abstract: Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: February 25, 2021Date of Patent: April 5, 2022Assignee: DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.Inventors: Matthew D. Montgomery, Krishna C. Veluru, Caterine Meza, Jerry W. Wood, Jaewook Song
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Patent number: 9810099Abstract: An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.Type: GrantFiled: June 29, 2015Date of Patent: November 7, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Ali Akturk, Jose L. Rodriguez, David L. Wasdell, John A. Orosa, Matthew D. Montgomery
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Patent number: 9593853Abstract: A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.Type: GrantFiled: February 20, 2014Date of Patent: March 14, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Matthew D. Montgomery, Richard C. Charron, Gary D. Snyder, William W. Pankey, Clinton A. Mayer, Benjamin G. Hettinger
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Publication number: 20160376929Abstract: An arrangement to control vibrations in a gas turbine exhaust diffuser is provided. The arrangement includes a protrusion coupled to a turbine exhaust cylinder strut for controlling shock induced oscillations in a gas turbine diffuser. The controlled shock induced oscillations minimize pressure fluctuations in the gas turbine exhaust diffuser such that an unsteadiness of the fluid flow surrounding the turbine exhaust cylinder strut is reduced. A method to fluid flow induced vibrations in a gas turbine diffuser is also provided.Type: ApplicationFiled: June 29, 2015Publication date: December 29, 2016Inventors: Ali Akturk, Jose L. Rodriguez, David L. Wasdell, John A. Orosa, Matthew D. Montgomery
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Patent number: 9528706Abstract: A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.Type: GrantFiled: December 13, 2013Date of Patent: December 27, 2016Assignee: SIEMENS ENERGY, INC.Inventors: Matthew D. Montgomery, Richard C. Charron, Jose L. Rodriguez, Bernhard W. Küsters, Jay A. Morrison, Alexander R. Beeck
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Patent number: 9127554Abstract: An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward.Type: GrantFiled: September 4, 2012Date of Patent: September 8, 2015Assignee: Siemens Energy, Inc.Inventors: Richard C. Charron, Matthew D. Montgomery
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Publication number: 20150233582Abstract: A duct arrangement in a can annular gas turbine engine. The gas turbine engine has a gas delivery structure for delivering gases from a plurality of combustors to an annular chamber that extends circumferentially and is oriented concentric to a gas turbine engine longitudinal axis for delivering the gas flow to a first row of blades A gas flow path is formed by the duct arrangement between a respective combustor and the annular chamber for conveying gases from each combustor to the first row of turbine blades The duct arrangement includes at least one straight section having a centerline that is misaligned with a centerline of the combustor.Type: ApplicationFiled: February 20, 2014Publication date: August 20, 2015Applicant: SIEMENS ENERGY, INC.Inventors: Matthew D. Montgomery, Richard C. Charron, Gary D. Snyder, William W. Pankey, Clinton A. Mayer, Benjamin G. Hettinger
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Patent number: 9091180Abstract: An airfoil assembly including an endwall and an airfoil extending from the into a gas flow path. The endwall includes upstream and downstream edges, and is defined on a platform structure having a front surface extending radially in a direction of a thickness of the platform structure. At least one fluid injection passage extends through the platform structure in a direction from the upstream edge toward the downstream edge of the endwall. The fluid injection passage has an outlet opening defined at the endwall and an inlet opening in fluid communication with a pressurized fluid source. The fluid injection passage extends at a shallow angle relative to a plane of the endwall wherein the fluid injection passage defines a passage axis passing through the front surface and the endwall for effecting energization of a boundary layer between the outlet opening and the airfoil leading edge.Type: GrantFiled: July 19, 2012Date of Patent: July 28, 2015Assignee: SIEMENS ENERGY, INC.Inventors: David J. Wiebe, Bruce L. Smith, Matthew D. Montgomery
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Publication number: 20150167986Abstract: A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.Type: ApplicationFiled: December 13, 2013Publication date: June 18, 2015Inventors: Matthew D. Montgomery, Richard C. Charron, Jose L. Rodriguez, Bernhard W. Küsters, Jay A. Morrison, Alexander R. Beeck
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Patent number: 8721291Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.Type: GrantFiled: July 12, 2011Date of Patent: May 13, 2014Assignee: Siemens Energy, Inc.Inventors: Ching-Pang Lee, Kok-Mun Tham, Paul H. Vitt, Stephen R. Williamson, Matthew D. Montgomery, Chander Prakash, Melissa Harris
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Publication number: 20140060000Abstract: An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward.Type: ApplicationFiled: September 4, 2012Publication date: March 6, 2014Inventors: Richard C. Charron, Matthew D. Montgomery
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Publication number: 20140023483Abstract: An airfoil assembly including an endwall and an airfoil extending from the into a gas flow path. The endwall includes upstream and downstream edges, and is defined on a platform structure having a front surface extending radially in a direction of a thickness of the platform structure. At least one fluid injection passage extends through the platform structure in a direction from the upstream edge toward the downstream edge of the endwall. The fluid injection passage has an outlet opening defined at the endwall and an inlet opening in fluid communication with a pressurized fluid source. The fluid injection passage extends at a shallow angle relative to a plane of the endwall wherein the fluid injection passage defines a passage axis passing through the front surface and the endwall for effecting energization of a boundary layer between the outlet opening and the airfoil leading edge.Type: ApplicationFiled: July 19, 2012Publication date: January 23, 2014Inventors: David J. Wiebe, Bruce L. Smith, Matthew D. Montgomery
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Patent number: 8585356Abstract: An electrode (54) in the tip (31) of a turbine or compressor blade (30), and a series of electrodes (68) in a shroud (36, 64) that surrounds a rotation path (33) of the blade tip. As the blade tip reaches each shroud electrode, a controller (74) activates an electrical potential between them that generates a plasma-induced gas flow (76) directed toward the pressure side (PS) of the airfoil. The plasma creates a seal between the blade tip and the shroud, and induces a gas flow that opposes a leakage gas flow (52) from the pressure side to the suction side (SS) of the blade over the blade tip (31).Type: GrantFiled: March 23, 2010Date of Patent: November 19, 2013Assignee: Siemens Energy, Inc.Inventors: David J. Wiebe, Matthew D. Montgomery
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Patent number: 8550768Abstract: A method for determining a preferred circumferential groove arrangement for a casing treatment of an axial flow compressor is disclosed. The method includes using the results from a three dimensional steady state computational fluid dynamic analysis to generate a flow field between a blade tip of a rotating blade and a compressor casing to determine the preferred circumferential groove arrangement. A stall margin for the axial flow compressor will be increased with the method.Type: GrantFiled: June 8, 2010Date of Patent: October 8, 2013Assignee: Siemens Energy, Inc.Inventor: Matthew D. Montgomery
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Patent number: 8500404Abstract: A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60-61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).Type: GrantFiled: April 30, 2010Date of Patent: August 6, 2013Assignee: Siemens Energy, Inc.Inventors: Matthew D. Montgomery, Chander Prakash
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Patent number: 8435001Abstract: Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.Type: GrantFiled: December 17, 2009Date of Patent: May 7, 2013Assignee: Siemens Energy, Inc.Inventors: Matthew D. Montgomery, Ching-Pang Lee, Chander Prakash
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Publication number: 20130017095Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.Type: ApplicationFiled: July 12, 2011Publication date: January 17, 2013Inventors: Ching-Pang Lee, Kok-Mun Tham, Paul H. Vitt, Stephen R. Williamson, Matthew D. Montgomery, Chander Prakash, Melissa Harris
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Patent number: 8276389Abstract: An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.Type: GrantFiled: April 28, 2011Date of Patent: October 2, 2012Assignee: Siemens Energy, Inc.Inventors: Richard C. Charron, Raymond S. Nordlund, Jay A. Morrison, Ernie B. Campbell, Daniel J. Pierce, Matthew D. Montgomery, Jody W. Wilson
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Publication number: 20110299979Abstract: A method for determining a preferred circumferential groove arrangement for a casing treatment of an axial flow compressor is disclosed. The method includes using the results from a three dimensional steady state computational fluid dynamic analysis to generate a flow field between a blade tip of a rotating blade and a compressor casing to determine the preferred circumferential groove arrangement. A stall margin for the axial flow compressor will be increased with the method.Type: ApplicationFiled: June 8, 2010Publication date: December 8, 2011Inventor: Matthew D. Montgomery