Patents by Inventor Gregory John Kajfasz
Gregory John Kajfasz 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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Publication number: 20210239132Abstract: A variable-cycle compressor includes: an axial-flow compressor, a flowpath downstream of the compressor, and at least one variable-cycle device operable to vary a choked flow capacity of the downstream flowpath. The compressor includes: a rotor having at least one rotor stage including a rotatable disk defining a rotor flowpath surface and an array of axial-flow rotor airfoils extending outward from the flowpath surface; at least one stator stage including a wall defining a stator flowpath surface, and an array of axial-flow stator airfoils extending away from the stator flowpath surface. At least one stage includes splitter airfoils alternating with the rotor or stator airfoils of the corresponding stage. At least one of a chord dimension of the splitter airfoils and a span dimension of the splitter airfoils is less than the corresponding dimension of the airfoils of the at least one stage.Type: ApplicationFiled: April 12, 2021Publication date: August 5, 2021Inventors: Anthony Louis DiPietro, JR., Andrew Breeze-Stringfellow, Gregory John Kajfasz
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Patent number: 9938984Abstract: A compressor apparatus includes: a rotor including: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface having an non-axisymmetric surface profile; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; and wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades.Type: GrantFiled: December 29, 2014Date of Patent: April 10, 2018Assignee: General Electric CompanyInventors: Anthony Louis DiPietro, Jr., Gregory John Kajfasz
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Patent number: 9874221Abstract: A compressor apparatus includes: a rotor having: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge, wherein the compressor blades have a chord dimension and are spaced apart by a circumferential spacing, the ratio of the chord to the circumferential spacing defining a blade solidity parameter; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades.Type: GrantFiled: December 29, 2014Date of Patent: January 23, 2018Assignee: General Electric CompanyInventors: Anthony Louis DiPietro, Jr., Gregory John Kajfasz
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Publication number: 20180017079Abstract: A variable-cycle compressor includes: an axial-flow compressor, a flowpath downstream of the compressor, and at least one variable-cycle device operable to vary a choked flow capacity of the downstream flowpath. The compressor includes: a rotor having at least one rotor stage including a rotatable disk defining a rotor flowpath surface and an array of axial-flow rotor airfoils extending outward from the flowpath surface; at least one stator stage including a wall defining a stator flowpath surface, and an array of axial-flow stator airfoils extending away from the stator flowpath surface. At least one stage includes splitter airfoils alternating with the rotor or stator airfoils of the corresponding stage. At least one of a chord dimension of the splitter airfoils and a span dimension of the splitter airfoils is less than the corresponding dimension of the airfoils of the at least one stage.Type: ApplicationFiled: July 15, 2016Publication date: January 18, 2018Inventors: Anthony Louis DiPietro, JR., Andrew Breeze-Stringfellow, Gregory John Kajfasz
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Publication number: 20170114796Abstract: A compressor apparatus includes: an inner flowpath surface; an outer flowpath surface; an array of stator airfoils extending between the inner and outer flowpath surfaces; and an array of airfoil-shaped splitter vanes extending from at least one of the inner and outer flowpath surfaces, the splitter vanes alternating with the stator airfoils, wherein at least one of a chord dimension of the splitter vanes at the roots thereof and a span dimension of the splitter vanes is less than a corresponding dimension of the stator airfoils.Type: ApplicationFiled: October 26, 2015Publication date: April 27, 2017Inventors: Anthony Louis DiPietro, JR., Gregory John Kajfasz
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Publication number: 20160186772Abstract: A compressor apparatus includes: a rotor including: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface having an non-axisymmetric surface profile; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; and wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades.Type: ApplicationFiled: December 29, 2014Publication date: June 30, 2016Inventors: Anthony Louis DiPietro, JR., Gregory John Kajfasz
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Publication number: 20160186773Abstract: A compressor apparatus includes: a rotor having: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge, wherein the compressor blades have a chord dimension and are spaced apart by a circumferential spacing, the ratio of the chord to the circumferential spacing defining a blade solidity parameter; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades.Type: ApplicationFiled: December 29, 2014Publication date: June 30, 2016Inventors: Anthony Louis DiPietro, JR., Gregory John Kajfasz
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Patent number: 9103213Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.Type: GrantFiled: February 29, 2012Date of Patent: August 11, 2015Assignee: General Electric CompanyInventors: Brian Chandler Barr, Brian David Keith, Gregory John Kajfasz, Prem Venugopal
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Patent number: 9085985Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.Type: GrantFiled: March 23, 2012Date of Patent: July 21, 2015Assignee: General Electric CompanyInventors: Brian Chandler Barr, Brian David Keith, Gregory John Kajfasz
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Publication number: 20130251520Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.Type: ApplicationFiled: March 23, 2012Publication date: September 26, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Brian Chandler Barr, Brian David Keith, Gregory John Kajfasz
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Publication number: 20130224027Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.Type: ApplicationFiled: February 29, 2012Publication date: August 29, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Brian Chandler Barr, Brian David Keith, Gregory John Kajfasz, Prem Venugopal