The present invention relates to a flow sleeve for controlling cooling airflow to an outer periphery of a combustion liner in a gas turbine engine.
Gas turbine engines are known, and typically include a compressor section that compresses air and delivers it downstream into a combustion section. The air is mixed with fuel in the combustion section and burned. Products of this combustion pass downstream towards a turbine section, to drive turbine rotors.
A combustion sleeve directs the products of combustion from the combustion section downstream toward the turbine rotors. The combustion liner becomes quite hot from the products of combustion. Thus, it is known to provide cooling air to an outer periphery of the combustion liner.
A part called a flow sleeve is mounted between an outer housing and the combustion liner, and provided with a plurality of openings. Cooling air is provided radially outwardly of the flow sleeve, and is directed through the holes at the outer periphery of the combustion liner. In this way, the combustion liner is cooled.
In one known flow sleeve, a plurality of tubular members extend about the holes, and from an inner periphery, to form conduits for controlling the direction in which the air is moved against the combustion liner. The tubular members add expense, and are complex to manufacture.
The present invention discloses a combustion liner to receive products of combustion in a gas turbine engine, and deliver the products of combustion downstream toward a turbine rotor. An outer housing is positioned radially outwardly of the combustion liner. A flow sleeve is positioned radially intermediate the outer housing and the combustion liner. The flow sleeve defines a chamber, radially outwardly of the flow sleeve, for receiving cooling air. A plurality of holes extend through the flow sleeve to deliver cooling air against an outer periphery of the combustion liner. A plurality of tabs are associated with at least some of the holes in the flow sleeve, and are positioned to extend radially inwardly on a downstream side of the holes.
The tabs control the air flow direction but are less expensive than the prior art.
These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
A combustion duct 20 for use in a gas turbine engine is illustrated in
As shown in
As can be appreciated from
As can be appreciated from
As can be appreciated, the tab ring 36 can be said to have an upstream side and a downstream side, and tabs 40 are at the downstream side. Notably, this description allows for a portion of the base to extend on a downstream side of the tabs 40. That is, the tabs 40 need not be at an extreme edge of the ring 36, and can still be said to be at the downstream side.
Although an embodiment of this invention has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.
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Number | Date | Country | |
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20100005805 A1 | Jan 2010 | US |