FIELD

The present subject matter relates generally to a vibration control assembly for use within a gas turbine engine, and a method for using the same.

BACKGROUND

Certain combustors in gas turbine engines may be particularly susceptible to combustion dynamics. Under certain engine operating conditions, significant transient pressure waves (“pings”) can be present, particularly in an annular combustor. These pressure waves, if of sufficient magnitude, may cause one or more components within a combustion section of the engine to vibrate, the vibration potentially resulting in high cycle fatigue of such components, before the hardware would need to be replaced under normal operations.

One known approach to combustor dynamic issues can involve careful mapping of problem regimes using test engines with multiple combustor instrumentation pressure sensors. Aircraft fuel schedules may then be developed from this process and subsequently programmed into engine control to address at least certain of these problem areas. Despite this mapping, however, subtle differences between engines may still adversely affect combustion dynamics behavior. These changes may be due to parameters including manufacturing variations, engine deterioration, fuel composition, or unexpected flight conditions.

Therefore, it may be beneficial to monitor combustor dynamics during fielded operation of the engine. Moreover, the inventor of the present disclosure has discovered that in addition to simply trying to prevent vibrations due to combustor dynamics, it may be beneficial to offset such vibrations to minimize an effect of such vibrations within the combustion section of the engine.

BRIEF DESCRIPTION

Aspects and advantages of the invention will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the invention.

In one exemplary aspect of the present disclosure, a method for operating a gas turbine engine is provided. The method includes receiving data indicative of an operational vibration within a section of the gas turbine engine; and providing electrical power to a shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate a canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.

In certain exemplary aspects the section of the gas turbine engine is a combustion section of the gas turbine engine.

For example, in certain exemplary aspects receiving data indicative of the operational vibration within the combustion section of the gas turbine engine includes receiving data from one or more accelerometers within the combustion section of the gas turbine engine.

For example, in certain exemplary aspects the one or more accelerometers are configured to measure a vibration of one or more of a combustor liner of a combustor within the combustion section of the gas turbine engine, a fuel nozzle within the combustion section of the gas turbine engine, a fuel manifold within the combustion section of the gas turbine engine, or a combustor case within the combustion section of the gas turbine engine.

In certain exemplary aspects receiving data indicative of the operational vibration within the section of the gas turbine engine includes receiving data indicative of at least one of a frequency, an amplitude, or a phase of the operational vibration.

For example, in certain exemplary aspects providing electrical power to the shaker mechanically coupled to one or more components of the section of the gas turbine engine to generate the canceling vibration includes generating a canceling vibration that is out of phase with the operational vibration.

In certain exemplary aspects providing electrical power to the shaker mechanically coupled to one or more components of the section of the gas turbine engine includes modulating the electrical power provided to the shaker in response to the received data indicative of the operational vibration within the section of the gas turbine engine.

For example, in certain exemplary aspects modulating the electrical power provided to the shaker includes modulating at least one of a voltage of the electrical power provided to the shaker, a current of the electrical power provided to the shaker, a frequency of the electrical power provided to the shaker, or a phase of the electrical power provided to the shaker.

For example, in certain exemplary aspects modulating the electrical power provided to the shaker includes modulating the electrical power provided to the shaker using a power amplifier.

In certain exemplary aspects the section of the gas turbine engine is the combustion section of the gas turbine engine, wherein the combustion section of the gas turbine engine includes an outer combustor case, and wherein the shaker is mechanically coupled to the outer combustor case.

In certain exemplary aspects the shaker is a first shaker, wherein the canceling vibration is a first canceling vibration, and wherein the method further includes providing electrical power to a second shaker mechanically coupled to one or more components of the combustion of the gas turbine engine to generate a second canceling vibration to reduce or minimize the operational vibration within the section of the gas turbine engine.

For example, in certain exemplary aspects providing electrical power to the second shaker mechanically coupled to one or more components of the section of the gas turbine engine includes modulating the electrical power provided to the second shaker in response to the received data indicative of the operational vibration within the section of the gas turbine engine.

In an exemplary embodiment of the present disclosure, a vibration management assembly of a gas turbine engine is provided. The vibration management assembly includes a sensor configured to measure a vibration within a combustion section of the gas turbine engine when installed in the gas turbine engine and a shaker configured to be mechanically coupled to the combustion section of the gas turbine engine when installed in the gas turbine engine. The vibration management assembly also includes a controller operably connected to the sensor and to the shaker, the controller including memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the vibration management assembly to perform functions. The functions include receiving data from the sensor indicative of an operational vibration within the combustion section of the gas turbine engine; and providing electrical power to the shaker to generate a canceling vibration to reduce or minimize the operational vibration within the combustion section of the gas turbine engine.

In certain exemplary embodiments receiving data from the sensor indicative of the operational vibration within the combustion section of the gas turbine engine includes receiving data from one or more accelerometers within the combustion section of the gas turbine engine.

For example, in certain exemplary embodiments the one or more accelerometers are configured to measure a vibration of one or more of a combustor liner of a combustor within the combustion section of the gas turbine engine, a fuel nozzle within the combustion section of the gas turbine engine, a fuel manifold within the combustion section of the gas turbine engine, or a combustor case within the combustion section of the gas turbine engine.

In certain exemplary embodiments receiving data from the sensor indicative of the operational vibration within the combustion section of the gas turbine engine includes receiving data indicative of at least one of a frequency, an amplitude, or a phase of the operational vibration.

For example, in certain exemplary embodiments providing electrical power to the shaker to generate the canceling vibration includes generating a canceling vibration that is out of phase with the operational vibration.

In another exemplary embodiment of the present disclosure, a gas turbine engine is provided. The gas turbine engine includes a compressor section; a turbine section; a combustion section disposed downstream of the compressor section and upstream of the turbine section; and a vibration management assembly. The vibration management assembly includes a sensor for sensing data indicative of a vibration within one of the compressor section, the turbine section, or the combustion section of the gas turbine engine and a shaker. The shaker is mechanically coupled to one or more components of the compressor section, the turbine section, or the combustion section to generate a canceling vibration to reduce or minimize the operational vibration within the compressor section, the turbine section, or the combustion section of the gas turbine engine during operation.

In certain exemplary embodiments the sensor of the vibration management is configured as an accelerometer.

In certain exemplary embodiments the vibration management assembly further includes a plurality of sensors, and wherein the plurality of sensors include at least one of a combustor liner sensor configured to measure data indicative of a vibration of a combustor liner, a fuel nozzle sensor configured to measure data indicative of vibration of a fuel nozzle, or a combustor case sensor configured to measure data indicative of a vibration of a combustor case.

These and other features, aspects and advantages of the present invention will become better understood with reference to the following description and appended claims. The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention.

