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).

  • TURBINE ABRADABLE AIR SEAL SYSTEM
    Publication number: 20180298776
    Abstract: An air scal 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: Application
    Filed: April 9, 2018
    Publication date: October 18, 2018
    Inventors: Christopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
  • Axial flowing cooling passages for gas turbine engine components
    Patent number: 10100667
    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: Grant
    Filed: January 15, 2016
    Date of Patent: October 16, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Anthony B. Swift, Paul M. Lutjen, Neil L. Tatman, Dominic J. Mongillo, Jr., Matthew A. Devore, Ken F. Blaney
  • Core component having toroidal structures
    Patent number: 10094225
    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: Grant
    Filed: January 25, 2016
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventors: Paul M. Lutjen, Gary L. Grogg
  • Multi-flow cooling passage chamber for gas turbine engine
    Patent number: 10060288
    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: Grant
    Filed: October 9, 2015
    Date of Patent: August 28, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dmitriy A. Romanov, Paul M. Lutjen
  • Gas turbine engine airfoil cooling passage turbulator pedestal
    Patent number: 10060267
    Abstract: A gas turbine engine component includes a structure that provides a cooling passage. The structure has a turbulator with a pedestal joining opposing first and second surfaces. The turbulator includes first and second legs spaced apart from one another and adjoining the pedestal. The first leg adjoins the second surface, and the second leg adjoins the first surface.
    Type: Grant
    Filed: April 25, 2014
    Date of Patent: August 28, 2018
    Assignee: United Technologies Corporation
    Inventor: Paul M. Lutjen
  • Seal
    Patent number: 10041366
    Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a substantially radially extending rail and a substantially axially extending leg, such that the seal has a substantially J-shaped cross-section.
    Type: Grant
    Filed: April 22, 2015
    Date of Patent: August 7, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy M. Davis, Paul M. Lutjen, Jeremy Drake
  • Blade outer air seal with cooling holes
    Patent number: 10018068
    Abstract: A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 1 herein, wherein the Cartesian coordinates are provided with respect to a point P which is at the center of an arc W and co-planer with a machined surface V. A blade outer air seal (BOAS) for a turbomachine can include a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in Table 2 herein, wherein the Cartesian coordinates are provided with respect to a point P? which is at the center of an arc W? and co-planer with a machined surface V?.
    Type: Grant
    Filed: January 13, 2015
    Date of Patent: July 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter J. Milligan, Paul M. Lutjen, Ken F. Blaney, Thurman C. Dabbs, Kevin J. Ryan
  • Seals for gas turbine engine
    Patent number: 10001022
    Abstract: The present disclosure relates to a first seal for an aircraft blade outer air seal (“BOAS”) comprising a first portion comprising a first channel and a second channel, and a second portion comprising a first projection and a second projection, wherein the first projection slidably couples to the first channel and the second projection slidably couples to the second channel. The first portion and/or the second portion may be coated with a low friction substance. The first portion may be coupled to a vane support and/or a BOAS, and the second portion may be coupled to a first OAS support. The first seal may enable a radial translation of the BOAS in response to an aircraft maneuver.
    Type: Grant
    Filed: April 21, 2014
    Date of Patent: June 19, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher W. Strock, Paul M. Lutjen
  • Blade outer air seal having partial coating
    Patent number: 9995165
    Abstract: A blade outer air seal member includes a distinct body that has two circumferential sides, a leading edge and a trailing edge, and a gas path side and a radially outer side opposite the gas path side. A ceramic coating is initially disposed on a portion of the gas path side. The ceramic coating includes a forward coating portion and an aft coating portion. The gas path side has a bare area axially separating the forward coating portion and the aft coating portion. The bare area excludes any of the ceramic coating. One or more cooling passages have an outlet that opens at the bare area. The cooling passage extends in the body in an axial direction under the ceramic coating.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: June 12, 2018
    Assignee: United Technologies Corporation
    Inventors: Christopher R. Joe, Paul M. Lutjen, Dominic J. Mongillo, Jr.
  • Conformal seal
    Patent number: 9957827
    Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an adjacent second seal section, each including a base and two extending legs defining respective first and second ends of the seal. At least the first seal section includes a first plurality of slots extending from the first end to the base and a second plurality of slots extending from the second end to the base.
    Type: Grant
    Filed: August 20, 2015
    Date of Patent: May 1, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy M Davis, Paul M Lutjen, Mark J. Rogers
  • Attachment arrangement for turbine engine component
    Patent number: 9951634
    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body having circumferential sides between a forward face and an aft face, each of the circumferential sides defining a mate face, an attachment member extending from the body, and a transition member adjacent to the body and the attachment member. The transition member and the body define a slot configured to receive a seal member. The transition member is sloped inwardly from one of the circumferential sides. A method of fabricating a gas turbine engine component is also disclosed.
    Type: Grant
    Filed: June 11, 2015
    Date of Patent: April 24, 2018
    Assignee: United Technologies Corporation
    Inventors: Carson A. Roy Thill, Russell E. Keene, Paul M. Lutjen
  • SLIDING SEAL
    Publication number: 20180106159
    Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a seal ring including a radially extending base and an axially-extending leg disposed in a seal cavity between first and second components. A retaining ring having a first leg and a second leg defining a cavity therebetween is disposed with a portion of the base and a portion of the first component contained therein, thereby providing loading forces to help the seal ring seal against both the first and second components. One or more rope seals are carried by the seal ring in an embodiment. Other combinations of seal rings, retaining rings, and rope seals are also disclosed.
    Type: Application
    Filed: December 15, 2017
    Publication date: April 19, 2018
    Inventors: Timothy M. Davis, Paul M. Lutjen
  • Turbine abradable air seal system
    Patent number: 9938849
    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: April 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
  • BLADE OUTER AIR SEAL SURFACE
    Publication number: 20180085880
    Abstract: A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
    Type: Application
    Filed: December 4, 2017
    Publication date: March 29, 2018
    Inventors: Paul M. Lutjen, Patrick D. Couture
  • Gas turbine engine components, blade outer air seal assemblies, and blade outer air seal segments thereof
    Patent number: 9926799
    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: Grant
    Filed: October 12, 2015
    Date of Patent: March 27, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dmitriy A. Romanov, Dominic J. Mongillo, Jr., Paul M. Lutjen
  • Blade outer air seal for a gas turbine engine
    Patent number: 9869202
    Abstract: A gas turbine engine includes a turbine section including a plurality of blade outer air seals (BOAS) disposed therein, the BOAS including a BOAS body including a plurality of cooling holes defined in substantial conformance with a set of Cartesian coordinates as set forth in at least one of Table 1 and Table 2.
    Type: Grant
    Filed: August 14, 2015
    Date of Patent: January 16, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Carson A. Roy Thill, Dominic J. Mongillo, Jr., Kevin D. Tracy, Jeffrey A. Perry, Thurman C. Dabbs
  • Sliding seal
    Patent number: 9845697
    Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a seal ring including a radially extending base and an axially-extending leg disposed in a seal cavity between first and second components. A retaining ring having a first leg and a second leg defining a cavity therebetween is disposed with a portion of the base and a portion of the first component contained therein, thereby providing loading forces to help the seal ring seal against both the first and second components. One or more rope seals are carried by the seal ring in an embodiment. Other combinations of seal rings, retaining rings, and rope seals are also disclosed.
    Type: Grant
    Filed: January 19, 2015
    Date of Patent: December 19, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy M. Davis, Paul M. Lutjen
  • Brush seal with single-layer mixed-diameter bristle pack
    Patent number: 9845884
    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: Grant
    Filed: March 17, 2016
    Date of Patent: December 19, 2017
    Assignee: United Technologies Corporation
    Inventors: Paul M. Lutjen, Jose R. Paulino
  • Blade outer air seal surface
    Patent number: 9833869
    Abstract: A blade outer air seal for a gas turbine engine having a surface that is eccentric with respect to the engine rotation centerline, and a method for creating same, are disclosed. Also, a method for grinding a work piece having nominal curvature defined by a work piece curvature centerline is disclosed, comprising the steps of: a) determining a desired surface profile for the work piece; b) providing a rotating grinding surface having a grinding rotation centerline; c) offsetting the grinding rotation centerline from the work piece curvature centerline; and d) applying the rotating grinding surface to the work piece while rotating the rotating grinding surface about the grinding rotation centerline to create the desired surface profile.
    Type: Grant
    Filed: February 10, 2014
    Date of Patent: December 5, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Paul M. Lutjen, Patrick D. Couture
  • 2 PLY W-SEAL USING DISSIMILAR MATERIALS
    Publication number: 20170343112
    Abstract: A metal gasket bellows seal includes a first ply comprised of a first material having a first yield strength. The metal gasket bellows seal also includes a second ply positioned adjacent to the first ply and comprised of a second material having a second yield strength that is less than the first yield strength.
    Type: Application
    Filed: May 31, 2016
    Publication date: November 30, 2017
    Inventors: TIMOTHY M. DAVIS, Terence P. Tyler, JR., Jose R. Paulino, Paul M. Lutjen