Patents by Inventor Judd Dodge Tressler
Judd Dodge Tressler 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: 6910868Abstract: Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 0.938 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.150 inches in directions normal to the surface of the airfoil.Type: GrantFiled: July 23, 2003Date of Patent: June 28, 2005Assignee: General Electric CompanyInventors: Susan Marie Hyde, Robert Romany By, Judd Dodge Tressler, Jon Conrad Schaeffer, Calvin Levy Sims
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Publication number: 20030223870Abstract: A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.Type: ApplicationFiled: May 31, 2002Publication date: December 4, 2003Inventors: Sean Robert Keith, Thomas Edward DeMarche, John Robert Staker, Judd Dodge Tressler
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Patent number: 6652220Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.Type: GrantFiled: November 15, 2001Date of Patent: November 25, 2003Assignee: General Electric CompanyInventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler
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Patent number: 6652235Abstract: A method for fabricating a rotor blade for a gas turbine engine facilitates reducing operating temperatures of a tip portion of the rotor blade. The method comprises forming an airfoil including a first sidewall and a second sidewall connected at a leading edge and a trailing edge to define a cavity therein, wherein the first and second sidewalls extend radially between a rotor blade root and a rotor blade tip plate, and forming a first tip wall extending from the rotor blade tip plate along the first sidewall, such that at least a portion of the first tip wall is at least partially recessed with respect to the rotor blade first sidewall to define a tip shelf that extends from the airfoil trailing edge towards the airfoil leading edge. A second tip wall is formed to extend from the rotor blade tip plate along the second sidewall.Type: GrantFiled: May 31, 2002Date of Patent: November 25, 2003Assignee: General Electric CompanyInventors: Sean Robert Keith, Thomas Edward DeMarche, John Robert Staker, Judd Dodge Tressler
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Patent number: 6609880Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more airfoil vane sidewall cooling than the second plurality of cooling openings.Type: GrantFiled: November 15, 2001Date of Patent: August 26, 2003Assignee: General Electric CompanyInventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler
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Patent number: 6602047Abstract: A turbine nozzle for a gas turbine engine includes a hollow airfoil vane including a first wall, a second wall, and a plurality of pins extending therebetween. The nozzle also includes at least one row of turbulators. The first and second walls are connected at a leading edge and a trailing edge. The first wall includes a plurality of slots extending towards the trailing edge, and the row of turbulators are substantially radially-aligned and extend between the plurality of slot and the pins.Type: GrantFiled: February 28, 2002Date of Patent: August 5, 2003Assignee: General Electric CompanyInventors: Joel Barreto, Andrew Charles Powis, Judd Dodge Tressler
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Publication number: 20030113201Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.Type: ApplicationFiled: November 15, 2001Publication date: June 19, 2003Inventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler
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Publication number: 20030091427Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more airfoil vane sidewall cooling than the second plurality of cooling openings.Type: ApplicationFiled: November 15, 2001Publication date: May 15, 2003Inventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler
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Patent number: 6382914Abstract: Radially extending cooling passages are provided in a turbine blade for flowing cooling air from a root portion to a tip portion of the blade. The passages are spaced from one another in a fore-to-aft direction. The aft cooling passages are smaller in diameter than the forward cooling passages. Refresher passageways extend from the larger-diameter passages to the smaller-diameter passages to supplement the cooling flow through outer portions of the aft cooling passages to cool the aft outer span portion of the blade.Type: GrantFiled: February 23, 2001Date of Patent: May 7, 2002Assignee: General Electric CompanyInventor: Judd Dodge Tressler
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Patent number: 6382908Abstract: A nozzle vane includes a row of trailing edge apertures and cooperating inboard slots joined in flow communication with a mid-chord cavity. An outboard slot is spaced outwardly from a respective last one of the inboard slots, and outboard of a respective last one of the trailing edge apertures. The outboard slot extends behind a fillet between the vane and a supporting band and is effective for backside cooling thereof.Type: GrantFiled: January 18, 2001Date of Patent: May 7, 2002Assignee: General Electric CompanyInventors: Sean Robert Keith, Judd Dodge Tressler, Steven Robert Brassfield, John Peter Heyward
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Patent number: 6382906Abstract: An impingement baffle for a turbine nozzle vane includes a perforate sleeve for discharging impingement air therethrough. A cap closes the sleeve at a top end, and includes an inlet hole. A spoolie cup includes a flange at the bottom thereof which is disposed atop the cap around the inlet hole for channeling air therein. A retainer is joined to the cap to loosely trap the cup flange thereatop for permitting limited lateral sliding movement thereof.Type: GrantFiled: June 16, 2000Date of Patent: May 7, 2002Assignee: General Electric CompanyInventors: Steven Robert Brassfield, Judd Dodge Tressler, Alan Lionel Webb
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Patent number: RE39320Abstract: An airfoil having extended life due to reduction in stresses. The stresses are reduced by extending the thermal barrier coating below the radius between the outer band perimeter and the inner flow path surfaces and tapering the coating thickness. This additional tapered thermal barrier coating reduces the temperature gradient across a region already having high mechanical stresses resulting from geometric considerations thereby lowering thermally-induced stresses so that low cycle fatigue life is improved.Type: GrantFiled: October 2, 2002Date of Patent: October 3, 2006Assignee: General Electric CompanyInventors: Glenn H. Nichols, Judd Dodge Tressler
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Patent number: RE39479Abstract: A turbine nozzle includes a plurality of vanes joined at opposite ends to outer and inner bands. The inner band has a forward hook which is segmented to reduce thermal mismatch. And, in additional embodiments the vane includes an impingement baffle having preferential cooling.Type: GrantFiled: February 5, 2003Date of Patent: January 23, 2007Assignee: General Electric CompanyInventors: Judd Dodge Tressler, Glenn H. Nichols
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Patent number: RE40658Abstract: A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.Type: GrantFiled: November 23, 2005Date of Patent: March 10, 2009Assignee: General Electric CompanyInventors: Andrew Charles Powis, Jonathan Philip Clarke, Judd Dodge Tressler