An exhaust diffuser system and method for a turbine engine includes an inner boundary and an outer boundary with a flow path defined therebetween The inner boundary is defined at least in part by a hub structure that has an upstream end and a downstream end The outer boundary may include a region in which the outer boundary extends radially inward toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure The hub structure includes at least one jet exit located on the hub structure adjacent to the upstream end of the tail cone The jet exit discharges a flow of gas substantially tangential to an outer surface of the tail cone to produce a Coanda effect and direct a portion of the exhaust flow in the diffuser toward the inner boundary

Turbine exhaust diffuser with a gas jet producing a coanda effect flow control

A transition duct assembly for a gas turbine engine includes an outer diameter surface and an inner diameter surface. A substantially annular flowpath having a radial offset is defined between the inner diameter surface and the outer diameter surface. A curvature distribution of the inner diameter surface includes a first region of increasing slope in a radial direction and a second region of decreasing slope in the radial direction adjacent to and downstream of the first region. The first and second regions are configured to reduce flow separation along the outer diameter surface of fluid traveling along the substantially annular flowpath.

Separation-resistant inlet duct for mid-turbine frames

A system that enables enhanced air flow to the air intake of an internal combustion engine having a turbocharger is disclosed. The air induction system includes a plenum or expansion chamber located within the area directly in front of the inlet of the turbocharger. Alternatively, the air induction system may include a diffuser and/or an expansion chamber for reducing the velocity of the air flow within the clean air duct in an area directly in front of the inlet of the turbocharger.

Apparatus for increasing induction air flow rate to a turbocharger

A vorticity reducing cowling for a diffuser augmented wind turbine assembly is provided. The diffuser augmented wind turbine assembly includes a shroud, a wind turbine disposed within the shroud, and a diffuser coupled to an outlet of the shroud. The wind turbine includes a wind turbine housing and a plurality of blades rotatably disposed within the wind turbine housing, wherein the plurality of blades providing a swept area. The cowling comprises a body disposed upstream of the plurality of blades. The body includes an inlet end defining a first opening, the first opening having a first area. The body includes an outlet end defining a second opening, the second opening having a second area that is less that the first area. The second area is less than the swept area of the plurality of the blades.

Vorticity reducing cowling for a diffuser augmented wind turbine assembly

A wind turbine for a diffuser augmented wind turbine assembly is provided. The wind turbine comprises a wind turbine housing, a hub mounted within the wind turbine housing, and a plurality of blades rotatably coupled with the hub and radially extending from the hub. The plurality of blades includes a first blade and a second blade, wherein the first blade includes a surface area and/or a maximum width that is greater than a surface area and/or a maximum width of the second blade to increase the efficiency of the diffuser augmented wind turbine assembly in variable speed winds.

Wind turbine with different size blades for a diffuser augmented wind turbine assembly

An annular diffuser has its inlet located at the exit of a last row of blades of a gas turbine having initially very slowly increasing cross-sectional area with distance to accommodate the diffusion produced by the decaying wakes in the diffuser so as to prevent flow separation from diffuser walls and as a result to foster the diffusion process and to increase the efficiency of the gas turbine. The rate of increase of cross-sectional area, which is much smaller than that appropriate in diffusers having uniform flow at their inlets, allows wakes which form near the trailing edges of the last turbine blades to dissipate while avoiding flow separation. In the diffuser of this invention, at a distance from inlet of one half of diffuser height at inlet, the cross-sectional area increase is smaller than 6.5% of the inlet cross-sectional area. This is equivalent to the corresponding two-dimensional straight-wall diffuser angle of, approximately 3.7 degrees.

Jerzy A. Owczarek

Papers

Annular flow diffusers for gas turbines