Abstract: A turbomachine is provided and includes a blade wheel having an outer radial portion defining first and second nested pockets, a blade having a root section, which is receivable in the first pocket and thereby securable in the first pocket in circumferential and radial dimensions and an insert, which is receivable in the second pocket and configured to secure the root section in an axial dimension with positive retention.

Abstract: The present invention provides a hula seal for use with a combustor. The hula seal includes a number of legs that define a number of slots. The slots may include a number of expansion slots.

Abstract: The present invention provides a hula seal for use with a combustor. The hula seal includes a number of legs that define a number of slots. The slots may include a number of expansion slots.

Abstract: A combustor liner for a gas turbine combustor includes a cooling hole formed in the liner that delivers cooling air into a combustion zone of the combustor. A stub is secured in the cooling hole and is structured to provide added stiffness to an inside edge of the cooling hole. The added stiffness reduces cracking caused by thermal fatigue and provides resistance against high cycle fatigue failures at high frequencies.

Abstract: A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly.

Abstract: A cooling arrangement for a turbine combustor liner includes a combustor liner; a flow sleeve surrounding at least a portion of the combustor liner with a flow annulus therebetween, the flow sleeve having a plurality of rows of cooling holes formed about a circumference thereof for directing cooling air into the flow annulus and toward the combustor liner. One or more of the cooling holes is fitted with a thimble extending in a radial direction toward the combustor liner, the thimble having a peripheral wall diverging in a direction of flow of the cooling air.

Abstract: A method facilitates assembling a gas turbine engine including a combustor assembly and a nozzle assembly. The method comprises providing a transition piece including a first end, a second end, and a body extending therebetween, where the body includes an inner surface, an opposite outer surface, coupling the first end of the transition piece to the combustor assembly, and coupling the second end of the transition piece to the nozzle assembly such that a turbulator extending helically over the outer surface of the transition piece extends from the transition piece first end to the transition piece second end to facilitate inducing turbulence to cooling air supplied to the combustor assembly.