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CN-121993296-A - Gas turbine engine and method of operating the same

CN121993296ACN 121993296 ACN121993296 ACN 121993296ACN-121993296-A

Abstract

An assembly for an aircraft includes a gas turbine engine including a turbine and a housing, and a system including a processor and a memory storing instructions to be executed by the processor to determine an exhaust temperature, which is a temperature of an airflow downstream of the turbine, based on data from one or more sensors disposed in the gas turbine engine, determine whether the exhaust temperature of the gas turbine engine is within a specified exhaust temperature threshold, and upon determining that the exhaust temperature exceeds the specified exhaust temperature threshold, control at least one of a motor or an active clearance control valve operatively connected to the turbine to adjust a clearance between two components of the gas turbine engine until a current exhaust temperature is within the specified exhaust temperature threshold.

Inventors

  • Timothy Leo Shelford
  • Cyril Moran
  • Kevin Richard Graziano
  • Timothy M. Kasberg
  • Donald Ira Goeper
  • Jason W. Holden

Assignees

  • 通用电气公司

Dates

Publication Date
20260508
Application Date
20251104
Priority Date
20241105

Claims (10)

  1. 1. An assembly for an aircraft, the assembly comprising: A gas turbine engine including a turbine and a casing, and A system comprising a processor and a memory, the memory storing instructions executable by the processor for: Determining an exhaust temperature based on data from one or more sensors disposed in the gas turbine engine, the exhaust temperature being a temperature of a gas flow downstream of the turbine; Determining whether the exhaust temperature of the gas turbine engine is within a specified exhaust temperature threshold, and Upon determining that the exhaust temperature exceeds the threshold of the specified exhaust temperature, controlling at least one of a motor or an active clearance control valve operatively connected to the turbine to adjust a clearance between two components of the gas turbine engine until a current exhaust temperature is within the threshold of the specified exhaust temperature.
  2. 2. The assembly of claim 1, wherein the instructions to control at least one of the motor or the active clearance control valve further comprise instructions to: Actuating the motor operatively connected to the turbine, or Power is drawn from the motor.
  3. 3. The assembly of claim 1, wherein the instructions further comprise instructions for maintaining the current gap above a gap floor.
  4. 4. The assembly of claim 1, wherein the instructions further comprise instructions for adjusting flow through the active lash control valve to adjust the lash.
  5. 5. The assembly of claim 1, wherein the instructions further comprise instructions for identifying a change in thrust output of the gas turbine engine and then determining whether the exhaust temperature of the gas turbine engine is within the threshold of the specified exhaust temperature.
  6. 6. The assembly of claim 1, wherein the instructions further comprise instructions for determining the specified exhaust gas temperature based on output from a machine learning program provided prior to the gas turbine engine initiating a take-off process.
  7. 7. The assembly of claim 1, wherein the instructions further comprise instructions for determining an operating condition of the gas turbine engine and determining the specified exhaust temperature based on the determined operating condition.
  8. 8. The assembly of claim 1, further comprising a temperature sensor downstream of the turbine, wherein the instructions further comprise instructions for determining the exhaust gas temperature based on data from the temperature sensor.
  9. 9. A method, comprising: Determining an exhaust gas temperature of a gas turbine engine, the exhaust gas temperature being a temperature of a gas flow downstream of a turbine of the gas turbine engine; Determining whether the exhaust temperature of the gas turbine engine is within a specified exhaust temperature threshold, and Upon determining that the exhaust temperature exceeds the threshold of the specified exhaust temperature, a gap between two components of the gas turbine engine is adjusted until a current exhaust temperature is within the threshold of the specified exhaust temperature.
  10. 10. The method of claim 9, wherein the gas turbine engine is a hybrid electric engine, and wherein the method further comprises at least one of: An electric motor that actuates a turbine operatively connected to the hybrid electric engine, or Power is drawn from the motor.

Description

Gas turbine engine and method of operating the same Technical Field The present disclosure relates to gas turbine engines and methods of operating the same. Background Turbine engines, including gas turbine or combustion turbine engines and hybrid electric gas turbine engines, are rotary engines that extract energy from a flow of combustion gases. Turbine engines typically include a compressor, a combustor, and a turbine arranged in a serial flow. The compressor compresses air supplied to a combustor where the air is mixed with fuel. The mixture is then ignited to produce hot combustion gases. The combustion gases are supplied to a turbine, which extracts energy from the combustion gases to drive a compressor, and to produce useful work to propel an aircraft in flight or to power a load (e.g., a generator). The hybrid electric turbine engine may also include at least one electric machine or motor that may be controlled to input or extract additional power to one rotating element of the turbine engine. Drawings A full and enabling disclosure of the present disclosure, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended figures, in which: FIG. 1 is a schematic illustration of an exemplary gas turbine engine provided in accordance with the present disclosure. FIG. 2 is a schematic illustration of a control system for a gas turbine engine. FIG. 3 is a schematic illustration of an active clearance control system for a gas turbine engine. FIG. 4 is a block diagram of an exemplary method of controlling gas turbine engine exhaust temperature. FIG. 5 is a block diagram of control of a hybrid electric gas turbine engine. FIG. 6 is a block diagram of active clearance control of a gas turbine engine. FIG. 7 is an operational block diagram of a gas turbine engine having a machine learning model for determining a specified exhaust temperature. FIG. 8 is a block diagram of an exemplary controller of a gas turbine engine. Detailed Description Reference will now be made in detail to embodiments of the disclosure, one or more examples of which are illustrated in the drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar reference numerals have been used in the drawings and description to refer to like or similar parts of the disclosure. The term "exemplary" as used herein refers to "serving as an example, instance, or illustration. Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Moreover, all embodiments described herein are to be considered as exemplary unless expressly specified otherwise. The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one component, and are not intended to represent the location or importance of the respective component. The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise. Furthermore, as used herein, the term "set" or "set of elements" may be any number of elements, including just one element. All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, rearward, etc.) are used for identification purposes only to aid the reader's understanding of the present disclosure, and do not create limitations, particularly as to the position, orientation, or use of the various aspects of the present disclosure as described herein. The terms "forward" and "aft" as used herein refer to relative positions within the hybrid electric gas turbine engine or carrier, and refer to the normal operational attitude of the hybrid electric gas turbine engine or carrier. For example, for a blade, forward refers to a location near the leading edge of the airfoil and aft refers to a location near the trailing edge. The terms "upstream" and "downstream" refer to the relative direction with respect to flow in a path. For example, for fluid flow, "upstream" refers to the direction from which the fluid flows and "downstream" refers to the direction in which the fluid flows. For example, when used in terms of fluid flow, forward/forward may refer to upstream and aft/backward may refer to downstream. In addition, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to a direction along a ray extending between a central longitudinal axis of the engine and the periphery of the engine. Unless otherwise indicated, connective references (e.g., attachment, coupling, co