Abstract: A wireguard subassembly includes a first circumferential segment defining a circumferential direction, a first near end, a first far end, and a first cleat portion disposed circumferentially between the first near end and the first far end; and a second circumferential segment defining a second near end, a second far end, and a second cleat portion disposed circumferentially between the second near end and the second far end. The second cleat portion is circumferentially aligned with the first cleat portion.

Abstract: A wireguard subassembly includes a first circumferential segment defining a proximate end including a ledge at least partially defining a notch; a second circumferential segment defining a distal end disposed adjacent the proximate end of the first circumferential segment; and a gusset member including a tab at least partially disposed in the notch on top of the ledge.

Abstract: A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced.

Abstract: A cutter system configured to sever elastomeric material of a non-pneumatic tire may include a cutter including a mounting fixture and a blade coupled to the mounting fixture. The cutter system may further include a driver assembly operably coupled to the mounting fixture of the cutter. The driver assembly may include a support member, and a cross-member operably coupled to the mounting fixture and the support member. The driver assembly may further include a first actuator operably coupled to the cross-member and the mounting fixture of the cutter, wherein the first actuator is configured to rotate the mounting fixture of the cutter relative to the cross-member. The driver assembly may further include a second actuator operably coupled to the cross-member and the support member, wherein the second actuator is configured to move the cross-member, such that the cutter reciprocates along a first axis relative to the support member.

Abstract: A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.

Abstract: A transition duct assembly for a turbine engine includes a transition duct with an inner liner removably received therein. The duct is hollow with an inner peripheral surface and an outer peripheral surface. The duct can have an inlet end and an outlet end. The inner peripheral surface of the duct can be convergent along a majority of the length of the duct when moving from the inlet end to the outlet end thereof. The liner is hollow body with an inner peripheral surface and an outer peripheral surface. The outer peripheral surface of the liner can be correspondingly convergent to the inner peripheral surface of the duct. The inner peripheral surface of the liner can define an internal flow passage through the assembly. Such a construction permits the use of different materials for the liner and the duct and can allow the liner to be readily removed and replaced.

Abstract: An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.

Abstract: A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.

Abstract: An arrangement (10) for conveying combustion gas from a plurality of can annular combustors to a turbine first stage blade section of a gas turbine engine, the arrangement (10) including a plurality of interconnected integrated exit piece (IEP) sections (16) defining an annular chamber (18) oriented concentric to a gas turbine engine longitudinal axis (20) upstream of the turbine first stage blade section. Each respective IEP (16) includes a first flow path section (40) receiving and fully bounding a first flow from a respective can annular combustor along a respective common axis (22) there between, and delivering a partially bounded first flow to a downstream adjacent IEP section (42). Each respective IEP further includes a second flow path section (112) receiving a partially bounded second flow from an upstream adjacent IEP (66) and delivering at least part of the second flow to the turbine first stage blade section.

Abstract: A reprographic machine having a plurality of operating subsystems employs a setup procedure that prevents use for copying until all subsystems reach operating conditions. To avoid the need for time lost in the setup procedure where a power shut down is short, a bypass system, which senses the duration of the shut down, is utilized to allow prompt return to the copy function. Heated elements, such as fuser rolls, motors, and the like can be utilized to provide a timing function, based on temperature decay characteristics relative to time. The sensed temperature can be used as a control parameter for allowing bypass of the setup procedures.