Chromalloy Gas Turbine Corporation

Daniel L Folkers

Vincent C Martling

Zhenhua Xiao

Adam Lee Hart

Charles A Ellis

Pedro Rivero

David G Parker

Richard Yu

Mariano Medrano

Paul Herber

John Bacile

A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of the transition duct, passes through a plurality of struts within the bellmouth, and is distributed to a passage located between the combustion liner and flow sleeve.

System and method for providing compressed air to a gas turbine combustor

A heat transfer mechanism is provided comprising a plurality of turbulators located along a surface of a body, such as a combustion liner. The turbulators have a first side with a first ramp angle, a second side with a second ramp angle, a height, and a base width, where the base width is a function of the height and where the turbulators are spaced an axial distance apart that is a function of the turbulator height.

Turbulator geometry for a combustion liner

An apparatus and method for mounting a combustion liner within a flow sleeve of a gas turbine combustion system is disclosed. A mounting system comprises a plurality of low-profile mounting tabs secured to a combustion liner where each of the mounting tabs are placed within slots of flow sleeve pegs when the combustion liner is installed in a flow sleeve. A plurality of liner stop brackets are removably secured to a flange of the flow sleeve and have an arm extending to be adjacent to a top contact surface of the mounting tabs. The mounting system reduces blockage to the surrounding airflow.

Axial stop configuration for a combustion liner

An apparatus and method for reducing the vibrations to a transition duct and improving the assembly and fit-up of a transition duct relative to a combustion system are disclosed. A damping member is provided between the transition duct and its mounting points to the gas turbine engine. The damping member comprises one or more layers of a composite material positioned between layers of sheet metal. An adjustable mounting system is also provided for the transition duct to allow for movement of a transition duct relative to the combustion liner.

Method and apparatus for mounting a transition duct in a gas turbine engine

A guide vane for use in a compressor discharge plenum of a gas turbine engine is disclosed. The guide vane comprises a guide support system, a first side panel, a second side panel, and a deflector panel secured to the mounting system and extending between the first side panel and the second side panel. The deflector panel has a curved profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1 where the X, Y, and Z values are in inches from a center point of a bottom surface of the deflector panel. The coordinate values are connected by smooth continuing arcs to form profile sections and the profile sections are joined together smoothly to form the curved profile of the guide vane.

Diffuser guide vane with deflector panel having curved profile

A system for retaining a cross fire tube in a multi-combustor gas turbine engine is disclosed. The system comprises a flow sleeve having a generally annular body, and a flange at a forward end thereof and having one or more recessed portions. A cross fire tube extends through one or more openings in the flow sleeve and is secured in place by a retention clip. The retention clip includes a plurality of fingers which engage the cross fire tube and a mounting plate engaging the one or more recessed portions of the flow sleeve flange so as to create a clip engagement having a lower profile than prior art configurations.

Cross fire tube retention system

A turbine nozzle having an airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, and within an envelope of approximately &#x2212;0.067 to +0.101 inches, where the X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 and convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form the airfoil shape. The X and Y values may also be scaled as a function of a first constant and the Z values may be scaled as a function of a second constant.

Growing community of inventors

Stuart, FL, United States of America

Daniel L Folkers