公开(公告)号：US10329929B2

公开(公告)日：2019-06-25

申请号：US15070703

申请日：2016-03-15

Applicant: United Technologies Corporation

Inventor： Nicholas Waters Oren ,  Steven D. Porter

IPC: F02C3/04 ,  F01D9/02 ,  F01D5/02 ,  F01D5/06 ,  F01D5/08 ,  F01D5/30

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a scallop formed along at least one surface of the groove, wherein the scallop is configured to provide a flow path, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

公开(公告)号：US10907477B2

公开(公告)日：2021-02-02

申请号：US16011056

申请日：2018-06-18

Applicant: United Technologies Corporation

Inventor： Nicholas Waters Oren

IPC: F01D5/02 ,  F04D29/66 ,  F16F15/34

Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance pin configured for insertion into an opening in the rotating component, a balance clip configured for installation to the rotating component over the balance pin to retain the balance pin in the opening via exertion of a retention force on the balance pin. A method of correcting an imbalance of a rotating assembly includes inserting a balance pin into a balancing opening in a rotating component of the rotating assembly, and installing a balance clip at the balancing opening over the balance pin to retain the balance pin in the balancing opening via exertion of a retention force by the balance clip on the balance pin.

公开(公告)号：US10385707B2

公开(公告)日：2019-08-20

申请号：US15070772

申请日：2016-03-15

Applicant: United Technologies Corporation

Inventor： Steven D. Porter ,  Nicholas Waters Oren

IPC: F01D9/02 ,  F01D5/02 ,  F02C3/04 ,  F01D5/06 ,  F01D5/30

Abstract: A disc of a gas turbine engine system is provided. The disc includes a disc bore including, an interstage coupling disposed on an axially extending surface at a peripheral edge of the disc bore that includes a protrusion that extends axially beyond an outer surface of the disc bore, and a groove formed on the axially extending surface of the disc bore wherein an aft surface of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.

公开(公告)号：US10358940B2

公开(公告)日：2019-07-23

申请号：US15632890

申请日：2017-06-26

Applicant: United Technologies Corporation

Inventor： Michael Lastrina ,  Nicholas Waters Oren

IPC: F01D5/08 ,  F01D25/12 ,  F16C3/02 ,  F16C37/00

Abstract: A turbine shaft comprising: a tubular body having an outer surface and an inner surface opposite the outer surface, the inner surface defining a hollow chamber within the tubular body, wherein the tubular body includes a first longitudinal axis concentric to the tubular body; and one or more shielded elliptical orifices, at least one shielded elliptical orifice comprising: an elliptical orifice in the tubular body including a major axis extending from a first side to a second side of the elliptical orifice, wherein the major axis is oriented at an angle parallel with a torque field of the tubular body; a first shielding orifice in the tubular body having a first axis collinear to the major axis; and a second shielding orifice in the tubular body having a second axis collinear to the major axis, wherein the elliptical orifice is located in between the first and second shielding orifice.

公开(公告)号：US20180371942A1

公开(公告)日：2018-12-27

申请号：US15632890

申请日：2017-06-26

Applicant: United Technologies Corporation

Inventor： Michael Lastrina ,  Nicholas Waters Oren

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D5/085 ,  F05D2220/32 ,  F05D2240/61 ,  F05D2240/63 ,  F05D2250/14 ,  F05D2250/314 ,  F05D2260/20 ,  F05D2260/60 ,  F05D2260/941 ,  F16C3/02 ,  F16C37/00 ,  F16C2326/43 ,  F16C2360/23

Abstract: A turbine shaft comprising: a tubular body having an outer surface and an inner surface opposite the outer surface, the inner surface defining a hollow chamber within the tubular body, wherein the tubular body includes a first longitudinal axis concentric to the tubular body; and one or more shielded elliptical orifices, at least one shielded elliptical orifice comprising: an elliptical orifice in the tubular body including a major axis extending from a first side to a second side of the elliptical orifice, wherein the major axis is oriented at an angle parallel with a torque field of the tubular body; a first shielding orifice in the tubular body having a first axis collinear to the major axis; and a second shielding orifice in the tubular body having a second axis collinear to the major axis, wherein the elliptical orifice is located in between the first and second shielding orifice.

公开(公告)号：US20170268351A1

公开(公告)日：2017-09-21

申请号：US15070696

申请日：2016-03-15

Applicant: United Technologies Corporation

Inventor： Nicholas Waters Oren ,  Steven D. Porter

IPC: F01D9/02 ,  F02C3/04 ,  F01D5/02

CPC classification number: F01D9/02 ,  F01D5/02 ,  F01D5/066 ,  F01D5/3015 ,  F02C3/04 ,  F05D2220/32 ,  F05D2260/30 ,  F05D2260/36

Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore, and wherein the groove extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.