公开(公告)号：US20140096536A1

公开(公告)日：2014-04-10

申请号：US13646822

申请日：2012-10-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brittany Travis ,  Crystal Monteiro ,  Sean Nolan ,  Rishon Saftler ,  John P. Virtue, JR. ,  Stephen A. Sarcich

IPC: F02C6/08 ,  B23P17/00 ,  F04D29/52

CPC classification number: F02C6/08 ,  F02C9/18 ,  F04D27/0207 ,  F04D27/0215 ,  F04D27/023 ,  F04D29/526 ,  F04D29/644 ,  Y10T29/49236

Abstract: A disclosed gas turbine engine includes a case for a case for a compressor section including a bleed air slot. The bleed air slot includes an inlet having a first area radially inward of an outlet having a second area with the second area being greater than the first area. The bleed air slot further includes a center portion disposed along a radial line extending from an axis of the engine and an elongated portion extending from the opening at an angle relative to a line normal to the radial line.

Abstract translation: 所公开的燃气涡轮发动机包括用于包括排气槽的压缩机部分的壳体的壳体。 放气空气狭槽包括入口，入口具有出口的径向向内的第一区域，其具有第二区域，第二区域大于第一区域。 排放空气狭槽还包括沿着从发动机的轴线延伸的径向线设置的中心部分和从开口以相对于径向线垂直的线成一定角度延伸的细长部分。

公开(公告)号：US20180327117A1

公开(公告)日：2018-11-15

申请号：US16034550

申请日：2018-07-13

Applicant: United Technologies Corporation

Inventor： Matthew D. Teicholz ,  Jeffrey W. Sutliff ,  William H. Greene, JR. ,  Kenneth J. White ,  Matthew R. Feulner ,  John P. Virtue, JR. ,  Jorn A. Glahn ,  Philip D. Hoover ,  Victor M. Pinedo ,  Jason B. Solomonides

IPC: B64F1/34 ,  F02C7/27 ,  F02C7/277 ,  B64D27/16

Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.

公开(公告)号：US20180265223A1

公开(公告)日：2018-09-20

申请号：US15985782

申请日：2018-05-22

Applicant: United Technologies Corporation

Inventor： Matthew D. Teicholz ,  Jeffrey W. Sutliff ,  William H. Greene, JR. ,  Kenneth J. White ,  Matthew R. Feulner ,  John P. Virtue, JR. ,  Jorn A. Glahn ,  Philip D. Hoover ,  Victor M. Pinedo ,  Jason B. Solomonides

IPC: B64F1/34 ,  F02C7/277 ,  B64D27/16 ,  F02C7/27

CPC classification number: B64F1/34 ,  B64D27/16 ,  F02C7/27 ,  F02C7/277 ,  F05D2220/323 ,  F05D2260/85 ,  F05D2270/303 ,  F05D2270/71

Abstract: A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (fmotoring), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Ntarget that is less than a speed to start the gas turbine engine, where tmotoring is a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of NtargetMin to NtargetMax for homogenizing engine temperatures.

公开(公告)号：US20170234231A1

公开(公告)日：2017-08-17

申请号：US15042368

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： John P. Virtue, JR. ,  Amy R. Grace ,  Parakrama Herath

IPC: F02C7/268 ,  B64D31/06 ,  B64F5/00

CPC classification number: F02C7/268 ,  B64D31/06 ,  F01D19/00 ,  F01D25/34 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/334

Abstract: A bowed rotor start mitigation system for a gas turbine engine is provided. The bowed rotor start mitigation system includes a controller operable to receive a vibration input indicative of an actual vibration level of the gas turbine engine and a speed input indicative of a rotor speed of the gas turbine engine. The controller generates a bowed rotor start mitigation request based on comparing the actual vibration level to a modeled vibration level at the rotor speed.

公开(公告)号：US20180230946A1

公开(公告)日：2018-08-16

申请号：US15343470

申请日：2016-11-04

Applicant: United Technologies Corporation

Inventor： John P. Virtue, JR. ,  Rishon Saftler ,  Frederick M. Schwarz

IPC: F02K3/068 ,  F04D29/64 ,  F01D11/18 ,  F02K3/02 ,  F02K3/06 ,  F02K3/075 ,  B64D27/00 ,  F02K3/11 ,  F01D25/16

CPC classification number: F02K3/068 ,  B64D2027/005 ,  F01D11/18 ,  F01D19/00 ,  F01D25/16 ,  F01D25/164 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/42 ,  F02K3/025 ,  F02K3/06 ,  F02K3/075 ,  F02K3/11 ,  F04D29/642 ,  F05D2220/3219 ,  F05D2220/36 ,  F05D2260/80 ,  F05D2260/84 ,  F05D2260/85 ,  Y02T50/671

Abstract: An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.

公开(公告)号：US20170233103A1

公开(公告)日：2017-08-17

申请号：US15042363

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： Matthew D. Teicholz ,  Jeffrey W. Sutliff ,  William H. Greene, JR. ,  Kenneth J. White ,  Matthew R. Feulner ,  John P. Virtue, JR. ,  Jorn A. Glahn ,  Philip D. Hoover ,  Victor M. Pinedo ,  Jason B. Solomonides

IPC: B64F1/34 ,  B64D27/16 ,  F02C7/27

CPC classification number: B64F1/34 ,  B64D27/16 ,  F02C7/27 ,  F02C7/277 ,  F05D2220/323 ,  F05D2260/85 ,  F05D2270/303 ,  F05D2270/71

Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.