Abstract: An acoustic damper for a rotary machine includes at least one wall, at least one inlet, at least one outlet, at least one separating wall, and at least one neck. The wall extends from the back side of a combustor front panel and defines a damping chamber. The inlet is defined within the wall and is oriented to channel a flow of air into the damping chamber. The outlet is defined within the back side of the front panel. The separating wall is oriented to separate the damping chamber into a first volume and a second volume. The first volume of the damping chamber is configured to damp an acoustic pressure oscillation at a first frequency. The second volume of the damping chamber is configured to damp the acoustic pressure oscillation at a second frequency. The neck extends through the separating wall and is axially offset from the outlet.

Abstract: A turbomachine includes a compressor and a turbine with a burner and a combustor between the compressor and the turbine. The burner is downstream of the compressor and upstream of the turbine. The burner is connected to the combustor at a front panel of the burner. The front panel includes a frame, a rim extending around a central aperture within the frame, and a seal segment. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.

Abstract: A rotary machine includes at least one burner including a front panel having a front side and an opposing back side. The acoustic damper includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one baffle. The wall extends from the back side of the front panel and defines a dampening chamber. The cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The baffle extends from the back side of the front panel and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.

Abstract: An acoustic damper for a rotary machine includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one cap. The at least one wall extends from a back side of a burner front panel such that the at least one wall partially defines a dampening chamber. The at least one cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The at least one outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The at least one cap is positioned at least partially over the at least one cooling air inlet and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.

Abstract: A turbomachine includes a compressor and a turbine with a burner and a combustor between the compressor and the turbine. The burner is downstream of the compressor and upstream of the turbine. The burner is connected to the combustor at a front panel of the burner. The front panel includes a frame, a rim extending around a central aperture within the frame, and a seal segment. The frame, the rim, and the seal segment are all integrally formed as a single unitary body.

Abstract: An acoustic damper for a rotary machine includes at least one wall, at least one inlet, at least one outlet, at least one separating wall, and at least one neck. The wall extends from the back side of a combustor front panel and defines a damping chamber. The inlet is defined within the wall and is oriented to channel a flow of air into the damping chamber. The outlet is defined within the back side of the front panel. The separating wall is oriented to separate the damping chamber into a first volume and a second volume. The first volume of the damping chamber is configured to damp an acoustic pressure oscillation at a first frequency. The second volume of the damping chamber is configured to damp the acoustic pressure oscillation at a second frequency. The neck extends through the separating wall and is axially offset from the outlet.

Abstract: A rotary machine includes at least one burner including a front panel having a front side and an opposing back side. The acoustic damper includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one baffle. The wall extends from the back side of the front panel and defines a dampening chamber. The cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The baffle extends from the back side of the front panel and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.

Abstract: An acoustic damper for a rotary machine includes at least one wall, at least one cooling air inlet, at least one outlet, and at least one cap. The at least one wall extends from a back side of a burner front panel such that the at least one wall partially defines a dampening chamber. The at least one cooling air inlet is defined within the back side of the front panel and is configured to channel a flow of cooling air into the dampening chamber. The at least one outlet is defined within the back side of the front panel and is configured to channel the flow of cooling air out of the dampening chamber. The at least one cap is positioned at least partially over the at least one cooling air inlet and is configured to reduce a velocity of the flow of cooling air within the dampening chamber.

Abstract: Aspects of the disclosure include a removable support for additive manufacture and methods and code for manufacturing and removing the same. A removable support for a laser-sintered component having at least one surface to connect to may include a support body, a first set of connectors, and a second set of connectors. The support body may have a first wing and a second wing, each with a distal surface and a lateral midline bisecting the distal surface. Each set of connectors may project from the distal surface on one side of the lateral midline of their respective wings to connect to the surface of the component while the distal surface also defines a connector-free portion on the other side of the lateral midline.

Abstract: Aspects of the disclosure include a machine and system for support removal and a laser-sintered component compatible with same. A laser-sintered component may have a component surface and at least one laser-sintered support extending from the component surface. A press may move a cutting surface along a cutting path adjacent to the component surface. The cutting surface has a shape complementary to the component surface and at least one cutting edge positioned to separate at least one laser-sintered support from the component surface as the cutting surface moves along the cutting path.

Abstract: Various embodiments include a tool for leakage testing a component, along with a related testing method. In some cases, the tool includes: a seal assembly for sealing an opening in the component, the seal assembly having: a front plate defining a pressure chamber around the opening in the component; a collar coupled with the front plate and surrounding sidewalls of the component; an insert extending between the front plate and the collar; an annular seal member between the collar and the insert; and a floating seal between the collar and the front plate, wherein the seal assembly is configured to flexibly seal the opening in the component; and a valve for controlling fluid flow into the pressure chamber during the leakage testing of the component.

Abstract: A damping system and apparatus are disclosed for dampening acoustic pressure oscillations of a gas flow in a combustor of a gas turbine engine having at least one combustor with a combustor liner. A second inner cap portion is disposed on the at least one combustor inner liner. The second inner cap portion can have a hot surface, a cold surface, at least one burner opening protruding from the cold surface, and at least one neck ring having an internal opening and protruding from the cold surface. At least one resonating tube having a resonating tube neck is integrated with and protruding from the at least one neck ring. The at least one resonating tube is disposed between adjacent burner openings, and is configured such that the radial dimension is greater than or equal to the axial dimension.

Abstract: A method of making a combustor cap assembly uses an additive manufacturing process of consecutively adding material in layers along an upstream axial build direction starting from a base side positioned transverse to the upstream axial build direction. The base side has at least one acoustic port. A bump side extends from the base side in the upstream axial build direction and has at least one damper projecting from the bump side. The damper has at least one inclined face forming an angle with the upstream axial build direction of less than or equal to 45 degrees. The resulting cap assembly includes a hot side with an acoustic port and a cold side with at least one damper with an inclined face and a damper chamber in communication with the acoustic port.

Abstract: Various embodiments include a tool for leakage testing a component, along with a related testing method. In some cases, the tool includes: a seal assembly for sealing an opening in the component, the seal assembly having: a front plate defining a pressure chamber around the opening in the component; a collar coupled with the front plate and surrounding sidewalls of the component; an insert extending between the front plate and the collar; an annular seal member between the collar and the insert; and a floating seal between the collar and the front plate, wherein the seal assembly is configured to flexibly seal the opening in the component; and a valve for controlling fluid flow into the pressure chamber during the leakage testing of the component.

Abstract: A self-breaking support for a vertically opposed first and second surfaces during additive manufacturing of an object is disclosed. The self-breaking support includes a first base coupled to the first surface and extending towards the second surface; a second base coupled to the second surface and extending towards the first surface; and a self-breaking link coupling the first base to the second base, the self-breaking link including a body and a weakened zone in the body. The self-breaking support breaks during cooling of the object without outside intervention, and can be left in the object.

Abstract: A method of making a combustor first inner cap device, and the device itself, is disclosed using the additive manufacturing process of consecutively adding material to a combustor first inner cap along an upstream axial build direction starting from a base side positioned transverse to the upstream axial build direction. Then adding material in consecutive steps to manufacture the first inner cap having at least one combustor that houses the first inner cap. The base side has at least one acoustic port. A bump side extends from the base side into the upstream axial build direction and has at least one damper positioned it. The damper has at least one overhang ledge forming an angle ? with the upstream axial build direction less than or equal to 45 degrees.

Abstract: A damping system and apparatus are disclosed for dampening acoustic pressure oscillations of a gas flow in a combustor of a gas turbine engine having at least one combustor with a combustor liner. A second inner cap portion is disposed on the at least one combustor inner liner. The second inner cap portion can have a hot surface, a cold surface, at least one burner opening protruding from the cold surface, and at least one neck ring having an internal opening and protruding from the cold surface. At least one resonating tube having a resonating tube neck is integrated with and protruding from the at least one neck ring. The at least one resonating tube is disposed between adjacent burner openings, and is configured such that the radial dimension is greater than or equal to the axial dimension.

Abstract: Aspects of the disclosure include a machine and system for support removal and a laser-sintered component compatible with same. A laser-sintered component may have a component surface and at least one laser-sintered support extending from the component surface. A press may move a cutting surface along a cutting path adjacent to the component surface. The cutting surface has a shape complementary to the component surface and at least one cutting edge positioned to separate at least one laser-sintered support from the component surface as the cutting surface moves along the cutting path.

Abstract: Aspects of the disclosure include a removable support for additive manufacture and methods and code for manufacturing and removing the same. A removable support for a laser-sintered component having at least one surface to connect to may include a support body, a first set of connectors, and a second set of connectors. The support body may have a first wing and a second wing, each with a distal surface and a lateral midline bisecting the distal surface. Each set of connectors may project from the distal surface on one side of the lateral midline of their respective wings to connect to the surface of the component while the distal surface also defines a connector-free portion on the other side of the lateral midline.

Abstract: Aspects of the disclosure include removable support packages for additive manufacture, in addition methods and code for manufacturing and removing the same. A removable support package for a laser-sintered component according to the present disclosure may include: a structure having opposing interior sidewalls, the opposing interior sidewalls defining a hollow interior of the structure; a plurality of supports extending between the opposing interior sidewalls of the structure; a first rod joining the plurality of supports at a first end proximal to one interior sidewall of the structure; and a second rod joining the plurality of supports at a second end proximal to another opposing interior sidewall of the structure.