公开(公告)号：US20200080428A1

公开(公告)日：2020-03-12

申请号：US16129457

申请日：2018-09-12

Applicant: United Technologies Corporation

Inventor： TIMOTHY J. JENNINGS ,  Mark F. Zelesky

IPC: F01D5/18 ,  F01D5/28 ,  F01D9/04

Abstract: A component for use in a gas turbine engine includes a channel configured to port a gas from an inlet along a flow path. The component further includes a wall defining an outlet configured to receive the gas, the wall forming an angle with the flow path that is between 60 degrees and 120 degrees, the outlet having a first portion with a first diameter and a second portion with a second diameter, the first portion configured to receive the gas before the second portion, and the first diameter being greater than the second diameter.

公开(公告)号：US10508549B2

公开(公告)日：2019-12-17

申请号：US14728514

申请日：2015-06-02

Applicant: United Technologies Corporation

Inventor： Wolfgang Balzer ,  Thomas J. Praisner ,  Atul Kohil ,  Mark F. Zelesky ,  Dominic J. Mongillo, Jr.

IPC: F01D5/14 ,  F01D5/02 ,  F01D5/18

Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.

公开(公告)号：US10450960B2

公开(公告)日：2019-10-22

申请号：US14860167

申请日：2015-09-21

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky ,  Joel H. Wagner ,  Shayan Ahmadian

IPC: F02C7/18 ,  F01D5/08

Abstract: A tangential on-board injector (TOBI) for a gas turbine engine is provided. The TOBI includes a body having an entrance and an exit, the body having an outer curved wall and defining an air passageway between the entrance and the exit and a purge cavity configured on an exterior surface of the body with a purge cavity entry fluidly connecting the air passageway to the purge cavity. The purge cavity is configured such that particles in an airflow through the passageway will enter the purge cavity.

公开(公告)号：US10422230B2

公开(公告)日：2019-09-24

申请号：US15008148

申请日：2016-01-27

Applicant: United Technologies Corporation

Inventor： Scott D. Lewis ,  Mark F. Zelesky ,  Dominic J. Mongillo

IPC: F01D5/18 ,  F23R3/00 ,  F01D9/02 ,  F01D5/22 ,  F01D11/08 ,  F01D25/24 ,  F01D25/12 ,  F02C7/18 ,  F01D9/06

Abstract: A gas turbine engine component having a cooling hole includes a first wall having a cooling hole inlet, a second wall generally opposite the first wall and having a cooling hole outlet, a metering section extending downstream from the inlet and having a hydraulic diameter (dh), and a diffusing section extending from the metering section to the outlet. The metering section includes a substantially convex first surface extending from a first end to a second end, a substantially concave second surface extending from a third end to a fourth end, and first and second curved portions connecting the ends of the first and second surfaces.

公开(公告)号：US20190271229A1

公开(公告)日：2019-09-05

申请号：US16408751

申请日：2019-05-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas N. Slavens ,  Mark F. Zelesky

IPC: F01D5/14 ,  B21K3/04 ,  F01D5/18 ,  B22F3/105 ,  B22F7/08 ,  B23K1/00 ,  B23K15/00 ,  B23K26/34 ,  B23K31/02 ,  B22F3/24 ,  B22D25/02 ,  B22D21/00 ,  B22F5/04 ,  B23K26/342 ,  B23K10/02 ,  B23K26/00

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.

公开(公告)号：US10393023B2

公开(公告)日：2019-08-27

申请号：US14860156

申请日：2015-09-21

Applicant: United Technologies Corporation

Inventor： Mark F. Zelesky

IPC: F02C7/18 ,  F01D5/08

Abstract: A tangential on-board injector for a gas turbine engine is provided. The tangential on-board injector includes a body having an entrance and an exit, the body having a curved shape and defining an air passageway between the entrance and the exit and an inlet extension connected to the entrance of the body, the inlet extension extending from the body and having an inlet configured to force air to change direction when entering the inlet of the inlet extension.

公开(公告)号：US20190078785A1

公开(公告)日：2019-03-14

申请号：US15698967

申请日：2017-09-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Atul Kohli ,  Benjamin D. Bellows ,  Brandon W. Spangler ,  David J. Hyland ,  Dennis M. Moura ,  Dustin W. Davis ,  Mark F. Zelesky ,  Ricardo Trindade ,  Stephen K. Kramer ,  Steven Bruce Gautschi ,  Trevor Rudy

IPC: F23R3/60 ,  F23R3/00

CPC classification number: F23R3/60 ,  F23R3/002 ,  F23R3/06 ,  F23R3/54 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044

Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.

公开(公告)号：US10202863B2

公开(公告)日：2019-02-12

申请号：US15162069

申请日：2016-05-23

Applicant: United Technologies Corporation

Inventor： Timothy M. Davis ,  Mark F. Zelesky ,  Michael G. McCaffrey

IPC: F01D11/00 ,  F16J15/02 ,  F16J15/44 ,  F01D11/08

Abstract: An annular ring for sealing a flow includes an inner ring and a tab. The tab extends radially and is configured to restrict axial movement of the seal.

公开(公告)号：US10156359B2

公开(公告)日：2018-12-18

申请号：US14655059

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark F. Zelesky ,  Joel H. Wagner ,  Tracy A. Propheter-Hinckley ,  Michael F. Blair ,  Thomas N. Slavens ,  Dominic J. Mongillo

IPC: F23R3/00 ,  F01D25/12 ,  F01D11/08 ,  F01D25/24 ,  F02C7/18 ,  F01D5/18 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.

公开(公告)号：US10101029B2

公开(公告)日：2018-10-16

申请号：US14673622

申请日：2015-03-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo ,  Mark F. Zelesky ,  Joel H. Wagner ,  William A. Sowa

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/60

Abstract: The present disclosure relates to combustor configurations, panels and components for a gas turbine engine. In one embodiment, a combustor for a gas turbine engine includes a support structure including a plurality of openings and a plurality of panels mounted to the structure. The plurality of panels define a combustion cavity of the combustor. Each panel includes a first wall configured to receive cooling air and a second wall configured to provide air flow for the cavity. The first and second walls form a cavity and include one or more elements for controlling the cooling effectiveness of each panel. Another embodiment is directed to a combustor panel including one or more elements for controlling cooling effectiveness. Another embodiment is directed to a support structure for a combustor of a gas turbine engine. Another embodiment is directed to configurations of panels including single walled portions or single walled panels.