公开(公告)号：US20160319837A1

公开(公告)日：2016-11-03

申请号：US15103817

申请日：2014-12-03

Applicant: Robert J. MORRIS ,  Carroll V. SIDWELL ,  Coy B. WOOD ,  Charles R. LEJAMBRE ,  UNITED TECHNOLOGIES CORPORATION

Inventor： Robert J. Morris ,  Carroll V. Sidwell ,  Coy B. Ellington ,  Charles R. Lejambre

IPC: F04D29/36 ,  F04D29/66 ,  F04D29/38 ,  F04D27/00 ,  F04D29/32

CPC classification number: F04D29/362 ,  F01D5/26 ,  F01D25/06 ,  F02C9/00 ,  F02C9/20 ,  F04D27/002 ,  F04D29/323 ,  F04D29/324 ,  F04D29/325 ,  F04D29/38 ,  F04D29/668 ,  F05B2220/33 ,  F05B2260/96 ,  F05B2270/20 ,  F05B2270/404 ,  F05B2270/80 ,  F05D2220/36 ,  F05D2260/96 ,  F05D2270/334 ,  F05D2270/44 ,  F05D2270/805 ,  Y02T50/673

Abstract: A gas turbine engine includes a plurality of blades, a sensor configured to detect vibration on one or more of the plurality of blades, and a controller coupled to the sensor and configured to adjust a blade incidence upon an onset of vibration being detected by the sensor wherein the adjustment of the blade incidence reduces the vibration.

Abstract translation: 燃气涡轮发动机包括多个叶片，传感器被配置为检测所述多个叶片中的一个或多个上的振动;以及控制器，耦合到所述传感器并且被配置成在所述传感器检测到的振动开始时调节叶片入射 其中叶片入射的调节降低了振动。

公开(公告)号：US20160319669A1

公开(公告)日：2016-11-03

申请号：US15038090

申请日：2014-12-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Robert J. Morris ,  Barry K. Benedict

IPC: F01D5/16 ,  F01D5/14

CPC classification number: F01D5/16 ,  F01D5/147 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2250/22 ,  F05D2250/23 ,  F05D2250/231 ,  F05D2260/96 ,  Y02T50/672

Abstract: A hollow blade of a gas turbine engine has a sacrificial elongated damper disposed slideably in a chamber for minimizing modes of vibration during operation. The chamber is defined between two opposing surfaces generally spanning radially outward from an axis of the engine and a face facing radially inward. The damper is constructed and arranged to make loaded contact with the face via a centrifugal force created by rotation of the engine.

Abstract translation: 燃气涡轮发动机的中空叶片具有可滑动地设置在腔室中的牺牲细长阻尼器，用于使操作期间的振动模式最小化。 腔室被限定在两个相对的表面之间，通常从发动机的轴线径向向外延伸，以及面向径向向内的面。 阻尼器被构造和布置成通过由发动机的旋转产生的离心力而与面部进行负载接触。

公开(公告)号：US11047397B2

公开(公告)日：2021-06-29

申请号：US15110889

申请日：2014-12-26

Applicant: United Technologies Corporation

Inventor： Richard K. Hayford ,  Robert J. Morris ,  Charles H. Warner ,  Charles P. Gendrich

IPC: F04D29/66 ,  F01D25/06 ,  F01D9/04 ,  F04D29/54 ,  F01D5/26

Abstract: A gas turbine engine includes a circumferential array of stator vanes that have first and second vanes with different vibrational frequencies than one another. The first vanes are arranged in circumferentially alternating relationship with the second vanes.

公开(公告)号：US20200040766A1

公开(公告)日：2020-02-06

申请号：US16055704

申请日：2018-08-06

Applicant: United Technologies Corporation

Inventor： Robert J. Morris

IPC: F01D25/16 ,  F02C7/06 ,  F16F7/01 ,  F16F9/30

Abstract: A gas turbine engine includes a fan rotating with a fan shaft, a compressor and a turbine section. The turbine section includes a fan drive rotor driving the fan through the fan shaft. At least one bearing is between an inner static case and the fan shaft. The inner static case is cantilever mounted to static structure, and has a forward end spaced in a forward direction toward the fan rotor from a cantilever mount. A damping assembly is associated with the inner static case.

公开(公告)号：US20180038285A1

公开(公告)日：2018-02-08

申请号：US15725720

申请日：2017-10-05

Applicant: United Technologies Corporation

Inventor： William E. Rosenkrans ,  Robert J. Morris

IPC: F02C9/20 ,  F01D17/08 ,  F01D17/14

Abstract: A gas turbine engine includes a fan section that has a fan. A fan casing surrounds the fan section. A compressor section defines an engine axis. A gear train reduces a rotational speed of the fan relative to a shaft. A low pressure turbine is coupled to the shaft. A nacelle extends along the engine axis and surrounds the fan casing, a bypass ratio of greater than 10. A variable area fan nozzle defines a discharge airflow area. A flutter sensing system includes a controller programmed to move the variable area fan nozzle to vary the discharge airflow area in response to detecting an airfoil flutter condition associated with adjacent airfoils of the fan.

公开(公告)号：US20170370220A1

公开(公告)日：2017-12-28

申请号：US15191885

申请日：2016-06-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Robert J. Morris ,  Anthony R. Parente ,  Frederick M. Schwarz ,  Carroll V. Sidwell

IPC: F01D5/00 ,  F04D29/32 ,  F01D21/00 ,  F04D29/54 ,  F01D5/12 ,  F01D21/14 ,  G01M15/14 ,  F01D9/02

CPC classification number: F01D5/005 ,  B23P6/002 ,  F01D5/12 ,  F01D9/02 ,  F01D21/003 ,  F01D21/14 ,  F04D29/324 ,  F04D29/542 ,  F05D2230/72 ,  F05D2230/80 ,  F05D2260/81 ,  F05D2260/82 ,  F05D2260/821 ,  F05D2270/09 ,  G01M15/14 ,  Y02T50/673

Abstract: A method of developing a suggested blend repair to an airfoil includes the steps of: (a) storing history with regard to a particular airfoil in a particular engine; (b) taking information with regard to new damage to the particular airfoil; (c) reaching an initial blend recommendation based upon step (b); (d) assessing whether the initial blend recommendation of step (c) would be appropriate to repair the new damage based upon a consideration of steps (a)-(c); and (e) reporting a final blend recommendation. An airfoil repair recommendation system is also disclosed.

公开(公告)号：US09483605B2

公开(公告)日：2016-11-01

申请号：US14134530

申请日：2013-12-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Robert J. Morris ,  Benjamin D. Hall ,  Lauren Gray ,  Ming-Ta Yang ,  Perry Bowes

IPC: G06F17/50 ,  F01D5/16 ,  F01D21/00

CPC classification number: G06F17/5086 ,  F01D5/16 ,  F01D21/003 ,  F05D2260/81 ,  F05D2260/961 ,  G06F17/5018 ,  G06F2217/76

Abstract: A novel probabilistic method for analyzing high cycle fatigue (HCF) in a design of a gas turbine engine is disclosed. The method may comprise identifying a component of the gas turbine engine for high cycle fatigue analysis, inputting parametric data of the component over a predetermined parameter space into at least one computer processor, using the at least one computer processor to build a plurality of flexible models of the component based on the parametric data of the component over the predetermined parameter space, using the at least one computer processor to build a plurality of emulators of the component based on the plurality of flexible models, and using the at least one computer processor to predict a probability of HCF based at least in part on the parametric data of the component over the predetermined parameter space and the plurality of emulators.

Abstract translation: 公开了一种用于分析燃气轮机发动机设计中的高循环疲劳（HCF）的新概念方法。 该方法可以包括识别用于高循环疲劳分析的燃气涡轮发动机的部件，使用至少一个计算机处理器将组件的预定参数空间的参数数据输入到至少一个计算机处理器中，以构建多个灵活模型 基于所述组件在所述预定参数空间上的参数数据，使用所述至少一个计算机处理器来基于所述多个灵活模型构建所述组件的多个仿真器，并且使用所述至少一个计算机处理器 至少部分地基于组件在预定参数空间和多个仿真器上的参数数据来预测HCF的概率。

公开(公告)号：US11434764B2

公开(公告)日：2022-09-06

申请号：US16520951

申请日：2019-07-24

Applicant: United Technologies Corporation

Inventor： Robert J. Morris ,  William D. Owen ,  Stuart K. Montgomery ,  Ron I. Prihar

IPC: F01D5/00 ,  F01D5/02

Abstract: A process for repairing an aircraft engine component includes receiving a plurality of component measurements of a damaged component, comparing the plurality of component measurements of the damaged component to a finite element model of an ideal component, generating a finite element model of the damaged component based at least partially on the comparison, determining a corrective material removal operation based at least in part on the finite element model of the damaged component, and removing material from the damaged component according to the corrective material removal operation, thereby creating a repaired component.

公开(公告)号：US20200032670A1

公开(公告)日：2020-01-30

申请号：US16044268

申请日：2018-07-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Robert J. Morris ,  Gary D. Roberge

IPC: F01D25/02 ,  F01D5/28 ,  F02K3/06 ,  H05B6/10

Abstract: An anti-ice arrangement for a gas turbine engine may comprise an engine static structure, a fan blade housed for rotation within the engine static structure, and a magnetic field source mounted in close proximity to the fan blade and configured for inducing eddy currents in the fan blade to increase a surface temperature of the fan blade.

公开(公告)号：US10316670B2

公开(公告)日：2019-06-11

申请号：US15038090

申请日：2014-12-04

Applicant: United Technologies Corporation

Inventor： Robert J. Morris ,  Barry K. Benedict

IPC: F01D5/16 ,  F01D5/14

Abstract: A hollow blade of a gas turbine engine has a sacrificial elongated damper disposed slideably in a chamber for minimizing modes of vibration during operation. The chamber is defined between two opposing surfaces generally spanning radially outward from an axis of the engine and a face facing radially inward. The damper is constructed and arranged to make loaded contact with the face via a centrifugal force created by rotation of the engine.