公开(公告)号：US20240141839A1

公开(公告)日：2024-05-02

申请号：US17976509

申请日：2022-10-28

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jeffrey Poissant ,  Robert Pontarelli ,  Cristina Crainic

IPC: F02C9/28 ,  F02C9/44

CPC classification number: F02C9/28 ,  F02C9/44 ,  F05D2220/323 ,  F05D2270/051 ,  F05D2270/304 ,  F05D2270/311 ,  F05D2270/313 ,  F05D2270/708

Abstract: A method and system for correlating engine thrust and engine thrust lever angle (TLA) during operation of a gas turbine engine powered aircraft is provided. The method includes: a) providing current flight conditions including a Mach number of the aircraft, altitude of the aircraft, and a TLA; b) determining a corrected fan speed value based on a sensed fan speed and flight conditions; c) determining a first corrected net thrust value based on the corrected fan speed value and the Mach number; d) determining a compensation factor using the corrected fan speed value, the Mach number, and the corrected net thrust value; e) determining a second corrected net thrust value as a function of the TLA; and f) correlating an engine fan speed to the TLA using the second corrected net thrust value as a function of the TLA and the compensation factor.

公开(公告)号：US11655725B2

公开(公告)日：2023-05-23

申请号：US17376639

申请日：2021-07-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jeffrey Poissant ,  Cristina Crainic

IPC: F01D11/24 ,  F01D25/12

CPC classification number: F01D11/24 ,  F01D25/12 ,  F05D2220/323 ,  F05D2270/301 ,  F05D2270/303 ,  F05D2270/312 ,  F05D2270/313 ,  F05D2270/44

Abstract: There is provided a system and a method for controlling a tip clearance between a turbine casing and turbine blade tips of an aircraft engine. At least one operational parameter of the aircraft engine is obtained. Based on the at least one operational parameter, a current value of the tip clearance and a target value of the tip clearance are determined. A limiting factor to be applied to the target value of the tip clearance is computed. The limiting factor is applied to the target value of the tip clearance to obtain a tip clearance demand for the aircraft engine. A tip clearance control apparatus of the aircraft engine is controlled based on a difference between the current value of the tip clearance and the tip clearance demand.

公开(公告)号：US12228085B2

公开(公告)日：2025-02-18

申请号：US17976509

申请日：2022-10-28

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jeffrey Poissant ,  Robert Pontarelli ,  Cristina Crainic

IPC: F02C9/16 ,  F02C9/28 ,  F02C9/44

Abstract: A method and system for correlating engine thrust and engine thrust lever angle (TLA) during operation of a gas turbine engine powered aircraft is provided. The method includes: a) providing current flight conditions including a Mach number of the aircraft, altitude of the aircraft, and a TLA; b) determining a corrected fan speed value based on a sensed fan speed and flight conditions; c) determining a first corrected net thrust value based on the corrected fan speed value and the Mach number; d) determining a compensation factor using the corrected fan speed value, the Mach number, and the corrected net thrust value; e) determining a second corrected net thrust value as a function of the TLA; and f) correlating an engine fan speed to the TLA using the second corrected net thrust value as a function of the TLA and the compensation factor.