Patents by Inventor Paul M. Lutjen

Paul M. Lutjen 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).

  • SHAPED COOLING PASSAGES FOR TURBINE BLADE OUTER AIR SEAL
    Publication number: 20170335706
    Abstract: A core assembly for fabricating an air cooled engine component for a gas turbine engine includes an end portion for defining passages within a side of an engine component. The end portion defines a first cross-section. A middle portion is spaced apart from the end portion and defines passages through a middle part of the engine component. The middle portion defines a second cross-section. One of the first cross-section and the second cross-section includes a first height greater than a second height. An air cooled engine component for a gas turbine engine and a gas turbine engine are also disclosed.
    Type: Application
    Filed: May 18, 2016
    Publication date: November 23, 2017
    Inventors: Timothy M. Davis, Paul M. Lutjen, Kevin J. Ryan
  • Break-in system for gapping and leakage control
    Patent number: 9803496
    Abstract: A blade outer air seal for use in a gas turbine engine having an axis of rotation includes a main body having a mating face configured to face, be positioned radially outward from, and be positioned adjacent to a rotor blade of the gas turbine engine. The blade outer air seal also includes an axial member extending aft from the main body, having a first radial face configured to face a second radial face of an outer diameter platform of a stator of the gas turbine engine, and having a first abradable material coupled to the first radial face.
    Type: Grant
    Filed: July 1, 2015
    Date of Patent: October 31, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Richard K. Hayford
  • Outer Airseal Insulated Rub Strip
    Publication number: 20170276007
    Abstract: A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer and a thermal barrier layer between the abradable layer and the substrate; and the thermal barrier layer comprises a ceramic and metallic phases within the ceramic.
    Type: Application
    Filed: March 23, 2016
    Publication date: September 28, 2017
    Inventors: Philip R. Rioux, Nicholas R Leslie, Paul M. Lutjen, Christopher W. Strock
  • BRUSH SEAL WITH SINGLE-LAYER MIXED-DIAMETER BRISTLE PACK
    Publication number: 20170268678
    Abstract: Aspects of the disclosure are directed to a brush seal comprising: a bristle pack that includes: a first plurality of bristles, each of the first plurality of bristles having a first dimension, and a second plurality of bristles, each of the second plurality of bristles having a second dimension that is different from the first dimension, where a ratio of the first dimension to the second dimension has a range of 2:1 to 5:1.
    Type: Application
    Filed: March 17, 2016
    Publication date: September 21, 2017
    Inventors: Paul M. Lutjen, Jose R. Paulino
  • Airfoil with variable profile responsive to thermal conditions
    Patent number: 9752442
    Abstract: An airfoil includes an airfoil body having a first section and a second section that differ in coefficient of thermal expansion by at least 10% and that each have a through-thickness that is 20% or greater than a through-thickness of the airfoil body. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions.
    Type: Grant
    Filed: September 16, 2016
    Date of Patent: September 5, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Richard K. Hayford, Paul M. Lutjen
  • Active clearance control system with zone controls
    Patent number: 9752451
    Abstract: An ACC system and method of using such for changing a turbine blade to BOAS gap on an aircraft engine is disclosed. The ACC system may comprise a first ring, a first supply line and a first flow control assembly. The first ring may be configured to substantially encircle a portion of a case assembly that is disposed around an aircraft engine turbine. The first ring may include a plurality of segments that each define a chamber, an inlet port and a plurality of outlet ports. At least a portion of the outlet ports may be configured to be disposed adjacent to the case. The first supply line may be operatively connected to a first segment of the plurality of segments. The first flow control assembly may be operatively connected to the first supply line and configured to meter the flow of cool air into the first segment.
    Type: Grant
    Filed: December 19, 2012
    Date of Patent: September 5, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ken F. Blaney, Paul M. Lutjen
  • C-SEAL BACKED BRUSH SEAL WITH A COMPRESSIBLE CORE
    Publication number: 20170248234
    Abstract: Aspects of the disclosure are directed to a brush seal assembly, comprising a compressible core, at least one wire wound around the core, and a backing plate that is substantially ‘c’ shaped or ‘u’ shaped that at least partially encases the at least one wire. Aspects of the disclosure are directed to a method comprising separating compressible cores with a spacer, winding wires around the cores and the spacer, and forming substantially ‘c’ shaped or ‘u’ shaped backings about the wires to obtain a package of brush seal assemblies.
    Type: Application
    Filed: February 25, 2016
    Publication date: August 31, 2017
    Inventors: Paul M. Lutjen, Jose R. Paulino
  • REPAIR MATERIAL PREFORM
    Publication number: 20170239763
    Abstract: A structural element for repairing a damaged component comprising a shaped cavity configured to receive the damaged component and a repair material, the shaped cavity comprising a material having a first melting point and the repair material comprising a material having a second melting point that is lower than the first melting point. The shaped cavity may comprise a preform for the damaged component. The preform may comprise a mold configured to reconstruct the shape of the damaged component. The repair material may comprise a first material and a second material, the second material having a melting point that is lower than the first material. The repair material may comprise a Nickel-Boron composition. The repair material may have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the damaged component.
    Type: Application
    Filed: May 9, 2017
    Publication date: August 24, 2017
    Applicant: United Technologies Corporation
    Inventors: Philip R. Belanger, Paul M. Lutjen, Richard K. Hayford
  • CHORDAL SEAL WITH SUDDEN EXPANSION/CONTRACTION
    Publication number: 20170226876
    Abstract: A static component for a gas turbine engine includes an axially extending body comprising a forward end and an aft end disposed axially downstream from the forward end. A rib is formed on at least one of the forward end and the aft end of the axially extending body and extending axially from the axially extending body. A recess is formed in the rib.
    Type: Application
    Filed: February 8, 2016
    Publication date: August 10, 2017
    Inventors: Philip Robert Rioux, Paul M. Lutjen
  • VARIABLE THICKNESS CORE FOR GAS TURBINE ENGINE COMPONENT
    Publication number: 20170211415
    Abstract: A gas turbine engine component has a body extending between two circumferential sides, and between a leading edge and a trailing edge. A refractory metal core within the body forms at least one cooling circuit to utilize fluid to cool the body. When the refractory metal core is removed from the body, the at least one cooling circuit includes an inlet, an outlet, and a passage that varies in cross-sectional area between the inlet and outlet. A method of manufacturing a gas turbine engine, a method of manufacturing a core, and a refractory metal core are also disclosed.
    Type: Application
    Filed: January 25, 2016
    Publication date: July 27, 2017
    Inventors: Anthony B Swift, Ken F. Blaney, Paul M. Lutjen, Neil L. Tatman, Dominic J. Mongillo
  • CORE COMPONENT HAVING TOROIDAL STRUCTURES
    Publication number: 20170211392
    Abstract: According to one embodiment of this disclosure a core includes a first end and a second end spaced generally opposite from the first end. The core further includes a stacking axis defined between the first end and second end and a first toroidal structure located between the first end and the second end. The first toroidal structure includes a first passage extending through the first toroidal structure in a first direction that is perpendicular to and passes through the stacking axis. The core also includes a second toroidal structure located between the first toroidal structure and the second end. The second toroidal structure includes a second passage extending through the second toroidal structure in a second direction. The first direction and the second direction are oriented along the stacking axis at a non-zero degree angle with respect to each other.
    Type: Application
    Filed: January 25, 2016
    Publication date: July 27, 2017
    Inventors: Paul M. Lutjen, Gary L. Grogg
  • GAS TURBINE ENGINE COMPONENTS WITH OPTIMIZED LEADING EDGE GEOMETRY
    Publication number: 20170204735
    Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body having a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The elongated transition portion has an axial length that is greater than a radial height. A gas turbine engine is also provided.
    Type: Application
    Filed: January 15, 2016
    Publication date: July 20, 2017
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: THOMAS J. PRAISNER, PAUL M. LUTJEN, KEN F. BLANEY, ANTHONY B. SWIFT, NEIL L. TATMAN, CHRISTOPHER M. JAROCHYM
  • AXIAL FLOWING COOLING PASSAGES FOR GAS TURBINE ENGINE COMPONENTS
    Publication number: 20170204742
    Abstract: A gas turbine engine component is provided. The gas turbine engine component comprises a main body and a leading edge cooling passage defined within the main body. The main body has a leading edge and a leading edge wall including an elongated transition portion extending between the leading edge and a proximate flowpath surface of the main body. The leading edge cooling passage comprises an axial flow cooling passage defined within the main body and adjacent to the leading edge wall and has a leading edge periphery that generally conforms to the elongated transition portion of the leading edge wall.
    Type: Application
    Filed: January 15, 2016
    Publication date: July 20, 2017
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Anthony B. SWIFT, Paul M. LUTJEN, Neil L. TATMAN, Dominic J. MONGILLO, JR., Matthew A. DEVORE, Ken F. BLANEY
  • Seal ring for gas turbine engines
    Patent number: 9708922
    Abstract: A seal assembly includes a first component, a second component, a first seal, a first shelf, a second shelf, and a second seal. The second component is adjacent to the first component and forms a cavity between the first and second components. The first seal spans the cavity. The first shelf extends axially from the first component and is located between the first seal and a hot gas path. The second shelf extends axially from the second component and is located between the first shelf and the hot gas path; the second shelf together with the first shelf forms a flow channel. The second seal conforms to the first shelf, sealing the flow channel.
    Type: Grant
    Filed: May 23, 2016
    Date of Patent: July 18, 2017
    Assignee: United Technologies Corporation
    Inventors: Timothy M. Davis, Mark J. Rogers, Paul M. Lutjen, Terence P. Tyler, Jr., Michael J. Bruskotter
  • Repair material preform
    Patent number: 9682449
    Abstract: A structural element and method for repairing a damaged portion of a metal component utilizes a preform configured to engage with the metal component and receive a repair material. The preform may be made of a material having a first melting point, and the repair material may be made of a material having a second melting point that is lower than the first melting point. The preform may be a mold configured to reconstruct the shape of the damaged portion of the metal component. The repair material may include a first material and an additive material, such as boron. The repair material may have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the metal component.
    Type: Grant
    Filed: April 15, 2015
    Date of Patent: June 20, 2017
    Assignee: United Technologies Corporation
    Inventors: Philip R. Belanger, Paul M. Lutjen, Richard K. Hayford
  • Turbine abradable air seal system
    Patent number: 9657584
    Abstract: An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.
    Type: Grant
    Filed: September 17, 2014
    Date of Patent: May 23, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
  • Airfoil with variable profile responsive to thermal conditions
    Patent number: 9650898
    Abstract: An airfoil includes an airfoil body having a first section and a second section that differ by coefficient of thermal expansion. The second section is arranged in thermomechanical juxtaposition with the first section such that the first section and the second section cooperatively thermomechanically control a profile of the airfoil body responsive to varying thermal conditions.
    Type: Grant
    Filed: December 27, 2012
    Date of Patent: May 16, 2017
    Assignee: United Technologies Corporation
    Inventors: Richard K. Hayford, Paul M. Lutjen
  • BLADE OUTER AIR SEAL
    Publication number: 20170107841
    Abstract: According to various embodiments, disclosed is a blade outer air seal assembly for a turbine engine comprising a main body portion that extends generally axially, with respect to a central axis of the turbine engine, from a leading edge portion of the main body to a trailing edge portion of the main body, wherein the leading edge portion includes a leading edge wall having a undercut profile along at least a portion of the leading edge wall, wherein the main body portion comprises cooling passages comprising a leading edge cooling passage adjacent to the leading edge wall, having a leading edge periphery on a side of the leading edge cooling passage adjacent to the leading edge wall, which generally conforms to the undercut profile of the leading edge wall.
    Type: Application
    Filed: October 16, 2015
    Publication date: April 20, 2017
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dmitriy A. Romanov, Paul M. Lutjen, Kevin J. Ryan, Ken F. Blaney
  • MULTI-FLOW COOLING PASSAGE CHAMBER FOR GAS TURBINE ENGINE
    Publication number: 20170101889
    Abstract: A cooling chamber in a gas turbine engine includes a first side surface, a second side surface, a bottom surface, and a top surface defining a chamber therein. The second side surface is angled at a first angle with respect to the first side surface, the chamber having an inlet end and an exit located downstream of the inlet end, wherein the chamber has a width that narrows from the inlet end toward the exit. An inlet is located in one of the top surface or the bottom surface at the inlet end of the chamber. At least one divider is located within the chamber, the at least one divider configured to separate an airflow flowing from the inlet to the exit into a first airflow and a second airflow. The at least one divider is angled at a second angle with respect to the first side surface.
    Type: Application
    Filed: October 9, 2015
    Publication date: April 13, 2017
    Inventors: Dmitriy A. Romanov, Paul M. Lutjen
  • GAS TURBINE ENGINE COMPONENTS, BLADE OUTER AIR SEAL ASSEMBLIES, AND BLADE OUTER AIR SEAL SEGMENTS THEREOF
    Publication number: 20170101881
    Abstract: A gas turbine engine component is provided. The gas turbine engine component has an internal cooling passage having first endwall and a second endwall. A primary inlet aperture is in fluid communication with a coolant supply and the first end of the internal cooling passage. An elongated rib is inside the internal cooling passage and proximate the primary inlet aperture. The elongated rib is configured to direct at least a portion of the coolant from the primary inlet aperture against a proximate one of the first or second endwall and then substantially reverse direction to flow downstream toward a second end of the internal cooling passage. A blade outer air seal (“BOAS”) assembly and a BOAS segment thereof are also provided.
    Type: Application
    Filed: October 12, 2015
    Publication date: April 13, 2017
    Applicant: United Technologies Corporation
    Inventors: DMITRIY A. ROMANOV, DOMINIC J. MONGILLO, JR., PAUL M. LUTJEN