FIELD OF THE TECHNOLOGY

The subject matter disclosed herein relates to a burner for a turbomachine. More specifically, the disclosure is directed to a front panel of a burner which is integrally formed.

BACKGROUND

Turbomachines, such as gas turbine engines, typically comprise an inlet section, a compression section, one or more burners, a combustion chamber, and a turbine section. The inlet section may include a series of filters, cooling coils, moisture separators, and/or other devices to purify and otherwise condition a working fluid (e.g., air) entering the gas turbine. The working fluid flows downstream from the inlet section to a compressor section where kinetic energy is progressively imparted to the working fluid to produce a compressed working fluid at a highly energized state. The compressed working fluid is mixed with a fuel from a fuel supply to form a combustible mixture within one or more burners. The combustible mixture is burned by the one or more burners to provide combustion gases having a high temperature and pressure to a combustion chamber. The combustion gases flow through a turbine of a turbine section wherein energy (kinetic and/or thermal) is transferred from the combustion gases to rotor blades, thus causing a shaft to rotate and produce work. For example, the rotation of the shaft may drive the compressor to produce the compressed working fluid. Alternately or in addition, the shaft may connect the turbine to a generator for producing electricity. Exhaust gases from the turbine flow through an exhaust section that connects the turbine to an exhaust stack downstream from the turbine. The exhaust section may include, for example, a heat recovery steam generator for cleaning and extracting additional heat from the exhaust gases prior to release to the environment.

The burners of such turbomachines typically adjoin the combustion chamber via a front panel of the burner. The front panel may also include damping features. A seal segment can be attached and welded to the front panel of the burner. The seal segment may be used to connect the front panel of the burner to a membrane seal and to an inner carrier to form a burner plenum.

Constructing and assembling the seal segment and the front panel of separate parts can introduce limitations into the design of the burner plenum. For example, the seal segment may conflict with or constrain the possible locations for the damping features on some front panels.

Accordingly, it is recognized in the art that there is a need for improved front panels for burners which provide sealing features and damping features.

BRIEF DESCRIPTION OF THE TECHNOLOGY

Aspects and advantages are set forth below in the following description, or may be obvious from the description, or may be learned through practice.

In one example embodiment of the present disclosure, a front panel for a burner of a turbomachine is provided. The turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending around the axial direction. The front panel includes a frame comprising an outer portion extending along the circumferential direction from a first side portion to a second side portion. The frame also includes an inner portion spaced apart from the outer portion along the radial direction by the first side portion and the second side portion. The inner portion of the frame extends along the circumferential direction from the first side portion to the second side portion. The front panel also includes a rim extending around a central aperture within the frame. The rim extends from the frame along the axial direction and is configured to join with a downstream end of the burner. The front panel also includes a seal segment connected to the inner portion of the frame. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.

In another example embodiment of the present disclosure, a turbomachine is provided. The turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending around the axial direction. The turbomachine includes a compressor, a turbine, a combustor disposed downstream from the compressor and upstream from the turbine, and a burner disposed downstream from the compressor and upstream from the turbine. The burner is connected to a front panel. The front panel of the burner includes a frame comprising an outer portion extending along the circumferential direction from a first side portion to a second side portion. The frame also includes an inner portion spaced apart from the outer portion along the radial direction by the first side portion and the second side portion. The inner portion of the frame extends along the circumferential direction from the first side portion to the second side portion. The front panel also includes a rim extending around a central aperture within the frame. The rim extends from the frame along the axial direction and is configured to join with a downstream end of the burner. The front panel also includes a seal segment connected to the inner portion of the frame. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.

These and other features, aspects and advantages of the present technology 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 technology and, together with the description, serve to explain the principles of the technology.

