The present disclosure relates generally to gas turbine compressor airfoils and more particularly to improved airfoil profiles for first stage compressor blades.
There are many design requirements for each stage of a gas turbine compressor in order for the stage to meet design goals including overall efficiency, airfoil loading, and mechanical integrity. Of particular concern is the design of the first stage blade of a compressor since it is an entry blade into the compressor.
Many airfoil profiles for gas turbines have been provided. See, for example EP0 887 513 B1, which discloses the stagger angle and camber angle of an airfoil of a turbine blade. Compressor design is however at a constant state of flux driven due to a desire to improve efficiency. There is therefore an advantage in providing airfoil designs that improve the balance of mechanical integrity and aerodynamic efficiency in these newly developed turbines and a desire to achieve airfoil designs to facilitate this development.
An exemplary embodiment provides an airfoil for a first stage compressor blade. The exemplary airfoil comprises a plurality of chord lengths, a plurality of stagger angles, and a plurality of camber angles at a plurality of divisions, respectively, along an airfoil height starting from a reference point at a first end of the airfoil extending to a second distal end. At a first division starting from the reference point, the airfoil height is 0.000 mm, the stagger angle is 18.300 degrees, the chord length is 128.000 mm, and the camber angle is 33.400 degrees. At a second division between the first division and the second distal end of the airfoil, the airfoil height is 43.890 mm, the stagger angle is 24.100 degrees, the chord length is 131.000 mm, and the camber angle is 28.900 degrees. At a third division between the second division and the second distal end of the airfoil, the airfoil height is 85.070 mm, the stagger angle is 28.778 degrees, the chord length is 133.800 mm, and the camber angle is 24.531 degrees. At a fourth division between the third division and the second distal end of the airfoil, the airfoil height is 142.690 mm, the stagger angle is 34.291 degrees, the chord length is 137.700 mm, and the camber angle is 18.702 degrees. At a fifth division between the fourth division and the second distal end of the airfoil, the airfoil height is 196.250 mm, the stagger angle is 38.600 degrees, the chord length is 141.000 mm, and the camber angle is 14.300 degrees. At a sixth division between the fifth division and the second distal end of the airfoil, the airfoil height is 246.520 mm, the stagger angle is 42.215 degrees, the chord length is 143.500 mm, and the camber angle is 11.500 degrees. At a seventh division between the sixth division and the second distal end of the airfoil, the airfoil height is 294.120 mm, the stagger angle is 45.647 degrees, the chord length is 145.200 mm, and the camber angle is 9.507 degrees. At an eighth division between the seventh division and the second distal end of the airfoil, the airfoil height is 324.620 mm, the stagger angle is 48.025 degrees, the chord length is 146.000 mm, and the camber angle is 8.255 degrees. At a ninth division between the eighth division and the second distal end of the airfoil, the airfoil height is 354.290 mm, the stagger angle is 50.500 degrees, the chord length is 354.390 mm, and the camber angle is 7.000 degrees.
Additional refinements, advantages, and features of the present disclosure are described in more detail below with reference to exemplary embodiments illustrated in the drawings, in which:
Exemplary embodiments of the present disclosure provide an improved airfoil having a unique profile for improved performance of a gas turbine compressor. This is accomplished by a unique airfoil profile defined in terms of stagger angle and camber angle.
According to an exemplary embodiment, the airfoil height can be scaled down by a factor of 1:1.2. In this way, unscaled and scaled aspects provide airfoils, which are suitable for operation at nominally 50 Hz and 60 Hz, respectively.
Other objectives and advantages of the present disclosure will become apparent from the following description, taken in connection with the accompanying drawings, which, by way of example, illustrate exemplary embodiments of the present disclosure.
Exemplary embodiments of the present disclosure are now described with reference to the drawings, wherein like reference numerals are used to refer to like elements throughout. In the following description, for purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the disclosure. However, the present disclosure may be practiced without these specific details, and the present disclosure is not limited to the exemplary embodiments disclosed herein.
The stagger angle γ is defined, as shown in
The camber angle Δβ, as shown in
As shown in
The stagger angle γ, camber angle Δβ and chord length CD, as defined in
An embodiment of the disclosure will now be described, by way of example, with reference to the dimensional characteristics defined in
In a further embodiment, the airfoil height AH is scaled down by a factor of 1:1.2 in order to be made suitable for operation at 60 Hz.
It will be appreciated by those skilled in the art that the present disclosure can be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The presently disclosed embodiments are therefore considered in all respects to be illustrative and not restricted. The scope of the disclosure is indicated by the appended claims rather than the foregoing description and all changes that come within the meaning and range and equivalence thereof are intended to be embraced therein.
Number | Name | Date | Kind |
---|---|---|---|
5980209 | Barry et al. | Nov 1999 | A |
20050031454 | Doloresco et al. | Feb 2005 | A1 |
20110135482 | Nash et al. | Jun 2011 | A1 |
Number | Date | Country |
---|---|---|
0887513 | Jul 2007 | EP |
Number | Date | Country | |
---|---|---|---|
20110286850 A1 | Nov 2011 | US |
Number | Date | Country | |
---|---|---|---|
61347044 | May 2010 | US |