Patent Application
20110305561
This invention is directed generally to turbine engines, and more particularly to cooling fluid feed systems in turbine engines.
Typically, gas turbine engines include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power. Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit. Typical turbine combustor configurations expose turbine blade assemblies to these high temperatures. As a result, turbine blades and turbine vanes must be made of materials capable of withstanding such high temperatures. Turbine blades, vanes and other components often contain cooling systems for prolonging the life of these items and reducing the likelihood of failure as a result of excessive temperatures.
Typically, turbine vanes extend radially inward from a vane carrier and terminate within close proximity of a rotor assembly. Turbine blades are typically attached to a rotor assembly and extend radially outward. Turbine blades are often supplied with cooling fluids from cooling channels in the rotor assembly. Often times, the cooling channels include leakage points at which leak cooling fluids from the cooling fluid channels, which negatively effects the efficiency of the turbine engine. Thus, there exists a need for a more efficient cooling fluid feed system for the rotor assembly of a gas turbine engine.
This invention relates to a cooling fluid metering system for a turbine blade of a gas turbine engine. The cooling fluid metering system may include a cooling channel positioned between a root of a turbine blade and an offset rotor sealing plate for supplying cooling fluids to turbine blades. At one point, a portion of the cooling channel may include a gap between the root and the offset rotor sealing plate. The gap may be sealed with teardrop shaped seal positioned within a teardrop shaped cavity at the gap. The cavity and seal may be positioned such that during operation, the seal is forced radially outward and into the gap, thereby effectively metering cooling fluid flow, which may be, but is not limited to, cooling air, through the cooling channel. By metering the cooling fluid flow through the cooling channel, the amount of leakage flow can be reduced, thereby improving the overall engine performance without reducing the component durability.
The cooling fluid metering system is useful in a turbine engine to meter cooling fluids therein. The turbine engine may include a rotor assembly including at least one row of turbine blades extending radially outward from a rotor, wherein a root of at least one turbine blade is coupled to a rotor disc and extends radially outward therefrom. One or more rotor sealing plates may be offset axially from the root of the turbine blade such that a gap is formed between the rotor sealing plate and the root of the turbine blade. The gap may form a portion of a cooling fluid channel of a turbine blade cooling system.
A first axially extending seal arm may extend axially from the root of the turbine blade towards the rotor sealing plate having a radially inner surface positioned at an acute angle such that an axially outer end of the first axially extending seal arm is radially outward from an intersection between the radially inner surface and the turbine blade. The cooling fluid metering system may also include a second axially extending seal arm extending axially from the rotor disc towards the rotor sealing plate having a radially outer surface positioned at an acute angle such that an axially outer end of the second axially extending seal arm is radially outward from an intersection between the radially outer surface and the turbine blade. Each of the first axially extending seal arm, the second axially extending seal arm and the rotor sealing plate may form a portion of a seal cavity having a teardrop shaped cross-section. The teardrop shaped seal may fill at least a portion of the seal cavity and may be positioned in the seal cavity for metering cooling fluid flow through the cooling fluid channel and past the gap. The teardrop shaped seal may also include one or more holes therein for metering flow past the seal.
The teardrop shaped seal may include a first outer surface that bears against the radially inner surface of the first axially extending seal arm and a second outer surface that bears against the radially outer surface of the second axially extending seal arm, wherein the first and second outer surfaces are coupled together at a tip. The teardrop shaped seal may be formed from a material configured to conform to the radially inner surface of the first axially extending arm and the radially outer surface of the second axially extending arm during operation as centrifugal forces force the teardrop shaped seal radially outward to seal the gap. In one embodiment, the teardrop shaped seal may be formed from a wire seal. A radially outermost portion of the teardrop shaped cavity may be located at the gap between the rotor sealing plate and the root of the turbine blade. An outermost point of the first axially extending seal arm in an axial direction may be generally aligned with an outermost point of the second axially extending seal arm in the axial direction. The rotor sealing plate may include a generally linear outer surface opposing the first and second axially extending arms.
An advantage of this invention is that by metering the cooling fluid flow through the cooling channel, the amount of leakage flow can be reduced, thereby improving the overall engine performance without reducing the component durability.
Another advantage of this invention is that the teardrop shaped seal seals the gap with precision and accuracy.
These and other embodiments are described in more detail below.
The accompanying drawings, which are incorporated in and form a part of the specification, illustrate embodiments of the presently disclosed invention and, together with the description, disclose the principles of the invention.
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A teardrop shaped seal 24 may be positioned in the seal cavity 26 for metering cooling fluid flow through the cooling fluid channel 14 and past the gap 22. The teardrop shaped seal 24 may be formed from a wire seal or other appropriate seal. As shown in
During use, cooling fluids, such as, but not limited to, air, may flow from the compressor and into the cooling channel 14. The cooling fluids may be pumped radially outward within the cooling channel 14. As the rotor assembly 30 begins to rotate and centrifugal forces develop, the centrifugal forces cause the teardrop shaped seal 24 to be pressed into the gap 22 such that the gap is sealed by the teardrop shaped seal 24. In one embodiment, the first outer surface 62 may bear against the radially inner surface 50 of the first axially extending seal arm 46 or the second outer surface 64 may bear against the radially outer surface 56 of the second axially extending seal arm 48, or both. As such, the cooling fluid flow through the cooling channel 14 is metered, and thus, the amount of leakage flow can be reduced, thereby improving the overall engine performance without reducing the component durability.
The foregoing is provided for purposes of illustrating, explaining, and describing embodiments of this invention. Modifications and adaptations to these embodiments will be apparent to those skilled in the art and may be made without departing from the scope or spirit of this invention.
This application claims priority to U.S. Provisional Patent Application No. 61/353,730, filed Jun. 11, 2010, the entirety of which is incorporated herein.
| Number | Date | Country | |
|---|---|---|---|
| 61353730 | Jun 2010 | US |
