公开(公告)号：US20160122552A1

公开(公告)日：2016-05-05

申请号：US14923538

申请日：2015-10-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Christopher W. Strock ,  Matthew E Bintz

IPC: C09D5/00 ,  F01D5/12 ,  C09D7/12 ,  F01D25/24 ,  C23C4/134 ,  C23C4/11 ,  F01D5/02 ,  F01D11/12

CPC classification number: C09D5/00 ,  C09D7/61 ,  C09D7/69 ,  C23C4/11 ,  C23C4/134 ,  F01D11/001 ,  F01D11/122 ,  F05D2300/121 ,  F05D2300/172 ,  F05D2300/173 ,  F05D2300/177 ,  F05D2300/2102 ,  F05D2300/2112 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/2282

Abstract: The present disclosure relates to an abrasive coating forming a seal material on components of gas turbine engines and a process for forming the abrasive coating. The abrasive coating may be applied to a structure in proximity to at least one section of the gas turbine engine having a plurality of airfoils. The abrasive coating in a first mode of operation of the gas turbine engine is capable of causing wearing of tips of the airfoils that come into contact with the abrasive coating and in a second mode of operation of the gas turbine engine has an interparticle strength sufficient to allow for fracture of the abrasive coating.

Abstract translation: 本公开涉及在燃气轮机发动机的部件上形成密封材料的研磨涂层和用于形成磨料涂层的方法。 研磨涂层可以施加到具有多个翼型件的燃气涡轮发动机的至少一个部分附近的结构。 在燃气涡轮发动机的第一操作模式中的磨料涂层能够引起与磨料涂层接触的翼型件的尖端磨损，并且在燃气涡轮发动机的第二操作模式中具有足够的颗粒间强度 允许研磨涂层的断裂。

公开(公告)号：US10767485B2

公开(公告)日：2020-09-08

申请号：US15864925

申请日：2018-01-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew E Bintz ,  Enzo DiBenedetto ,  Paul E Coderre

IPC: F01D5/06 ,  F01D5/08 ,  F02C7/18 ,  F02C7/141 ,  F04D29/58 ,  F04D29/32 ,  F01D11/02 ,  F01D11/00

Abstract: A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.

公开(公告)号：US10415465B2

公开(公告)日：2019-09-17

申请号：US15851285

申请日：2017-12-21

Applicant: United Technologies Corporation

Inventor： Matthew E Bintz ,  Enzo DiBenedetto

IPC: F02C3/08 ,  F02C7/28 ,  F02C9/18

Abstract: An auxiliary compressor for a gas turbine engine is disclosed. The auxiliary compressor includes a first axial rotor, a second axial rotor positioned downstream of the first axial rotor, and a centrifugal impeller positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.

公开(公告)号：US20190195127A1

公开(公告)日：2019-06-27

申请号：US15851285

申请日：2017-12-21

Applicant: United Technologies Corporation

Inventor： Matthew E Bintz ,  Enzo DiBenedetto

IPC: F02C3/08 ,  F02C9/18 ,  F02C7/28

CPC classification number: F02C3/08 ,  F02C6/08 ,  F02C7/28 ,  F02C9/18 ,  F05D2220/32 ,  F05D2220/3218 ,  F05D2240/20

Abstract: An auxiliary compressor for a gas turbine engine is disclosed. The auxiliary compressor includes a first axial rotor, a second axial rotor positioned downstream of the first axial rotor, and a centrifugal impeller positioned intermediate the first axial rotor and the second axial rotor and operably coupled to the first axial rotor.