초록 ▼

A transition duct in an advanced heavy duty gas turbine engine is cooled by impingement jets formed by apertures in a sleeve spaced a distance from the surface to be cooled. The sleeve is configured so as to duct spent impingement air towards the combustor, where it can be subsequently used for mixi

A transition duct in an advanced heavy duty gas turbine engine is cooled by impingement jets formed by apertures in a sleeve spaced a distance from the surface to be cooled. The sleeve is configured so as to duct spent impingement air towards the combustor, where it can be subsequently used for mixing with, and combustion of, the fuel, or for cooling of the combustor. The distance between the impingement sleeve and the transition duct surface is varied to control the velocity of air crossflow from spent impingement air in order to minimize the pressure loss due to crossflow. The cross-sectional areas of the apertures are varied to project impingement jets over the various distances and crossflow velocities. Generally, larger aperture areas are used with larger distances. The distance between the impingement sleeve and the transition duct systematically increases towards the combustor as the quantity of spent impingement air increases to a maximum value at the intersection of the combustor and the transition duct. The combination of variations in distance, aperture size, and inter-aperture spacing is utilized to vary the impingement cooling intensity to compensate for the variable internal heat load and also to produce the desired temperature distribution over the surface of the transition duct according to design requirements. The aforementioned variations are optimized to minimize the air flow pressure drop ahead of the combustion system which achieving the required cooling intensity according to design requirements.

대표청구항 ▼

An impingement cooling apparatus for cooling a surface of a transition duct disposed between a combustor and a turbine stage of a gas turbine engine, said transition duct being disposed in a compressed air plenum, comprising: an impingement sleeve surrounding said transition duct and spaced a distan

An impingement cooling apparatus for cooling a surface of a transition duct disposed between a combustor and a turbine stage of a gas turbine engine, said transition duct being disposed in a compressed air plenum, comprising: an impingement sleeve surrounding said transition duct and spaced a distance therefrom to form a flow volume therebetween: a plurality of apertures in said impingement sleeve; each of said plurality of apertures having an area: adjacent ones of said plurality of apertures being separated by a spacing: a closed end at a turbine end of said flow volume; an exit at a combustor end of said flow volume; a flow sleeve within the compressed air-plention surrounding said combustor; a flared entry portion at an end of said flow sleeve overlapping said exit and forming an aerodynamic converging shape therebetween; a flow of air through said aerodynamic converging shape flowing toward said combustor being effective to reduce a pressure at said exit below a pressure in said compressed air plenum whereby a pressure drop across said impingement sleeve produces an impingement jet of air from each of said plurality of apertures directed toward said transition duct: and at least one of said distance, said area and said spacing being non-uniform over said impingement sleeve to control a cooling in said surface.