TEAR-DROP SHAPED PART-SPAN SHROUD
A rotatable blade for use in a turbomachine includes an airfoil portion having a leading edge, a trailing edge a radially-inner end and a radially-outer end; a root section affixed to the radially-inner end of the airfoil portion. A part-span shroud is located on the airfoil portion between the root section and the radially-outer end. The part-span shroud is substantially tear-drop shaped such that its cross-sectional shape has a maximum thickness located within 20 to 40% of a chord length extending between leading and trailing edges of the part-span shroud, as measured from the leading edge of the part-span shroud.
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The invention relates generally to rotating blades for use in turbomachines. More particularly, the invention relates to a rotating blades provided with part-span shrouds between adjacent blades.
The fluid flow path of a turbomachine such as a steam or gas turbine is generally formed by a stationary casing and a rotor. In this configuration, a number of stationary vanes are attached to the casing in a circumferential array, extending radially inward into the flow path. Similarly, a number of rotating blades are attached to the rotor in a circumferential array and extending radially outward into the flow path. The stationary vanes and rotating blades are arranged in alternating rows so that a row of vanes and the immediate downstream row of blades form a “stage”. The vanes serve to direct the flow path so that it enters the downstream row of blades at the correct angle. Airfoils of the blades extract energy from the working fluid, thereby developing the power necessary to drive the rotor and the load attached thereto.
The blades of the turbomachine may be subject to vibration and axial torsion as they rotate at high speeds. To address these issues, blades typically include part-span shrouds disposed on the airfoil portions at an intermediate radial distance between the tip and the root section of each blade. The part-span shrouds are typically affixed to each of the pressure (concave) and suction (convex) sides of each airfoil, such that the part-span shrouds on adjacent blades matingly engage and frictionally slide along one another during rotation of the rotor.
BRIEF DESCRIPTION OF THE INVENTIONIn one exemplary but nonlimiting embodiment, there is provided a rotatable blade for a turbomachine, comprising an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end; a root section affixed to the radially-inner end of the airfoil portion; and a substantially tear-drop shaped part-span shroud located on the airfoil portion between the root section and the radially outer end, wherein the part-span shroud is provided with cross-sectional shape having a maximum thickness located within 20 to 40% of a chord length extending from a leading edge of the part-span shroud to a trailing edge of the part-span shroud, as measured from the leading edge of the part-span shroud.
In another exemplary aspect, there is provided a turbomachine comprising a rotor rotatably mounted within a stator, the rotor including a shaft; at least one rotor wheel mounted on the shaft, each of the at least one rotor wheels including a plurality of radially outwardly extending blades mounted thereon; and wherein each blade includes an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end, a pressure side and a suction side; a root section at the radially-inner end of the airfoil portion; and a part-span shroud located on the airfoil portion between the root section and the radially outer end, on the pressure side and the suction side, wherein the part-span shroud is provided with a substantially tear-drop cross-sectional shape having a maximum thickness located within 20 to 40% of a chord length extending between a leading edge of the part-span shroud and a trailing edge of the part-span shroud, as measured from the leading edge of the part span shroud.
In still another exemplary aspect, a turbomachine comprising a rotor rotatably mounted within a stator, the rotor including a shaft; at least one rotor wheel mounted on the shaft, each of the at least one rotor wheels including a plurality of radially outwardly extending blades mounted thereon; and wherein each blade includes an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end, a pressure side and a suction side; a root section at the radially-inner end of the airfoil portion; and a part-span shroud located on the airfoil portion between the root section and the radially outer end, on the pressure side and the suction side, wherein the part-span shroud is provided with a tear-drop cross-sectional shape having a maximum thickness located at 31%-37% of a chord length extending between a leading edge of the part-span shroud and a trailing edge of the part span shroud, as measured from the leading edge of the part-span shroud; and wherein the part-span shroud is disposed on the airfoil portion between about 40% and 80% of a radial height of the airfoil portion as measured from the root section of the blade.
These and other aspects, advantages and salient features of the invention will become apparent from the following detailed description, in conjunction with the drawings identified below.
It is noted that the drawings of the disclosure are not necessarily to scale. The drawings are intended to depict only typical aspects of the disclosure, and therefore should not be considered as limiting the scope of the disclosure.
DETAILED DESCRIPTION OF THE INVENTIONAs described below, embodiments of the invention are applicable to both steam and gas turbine engines employed in the production of electricity. It is understood, however, that the teachings are equally applicable to other electric machines including, but not limited to, gas turbine engine compressors, fans and gas turbines used in aviation. It should also be apparent to those skilled in the art that the present invention is applicable to differently scaled versions of the machines mentioned above.
In operation, steam 24 enters an inlet 26 of turbine 10 and is channeled through stationary vanes 22. Vanes 22 direct the steam 24 downstream against the blades 20. The steam 24 passes through the remaining stages, imparting a force on blades 20 causing shaft or rotor 14 to rotate. At least one end of turbine 10 may extend axially away from rotor 12 via shaft 14 and may be attached to a load or other machinery (not shown) such as, but not limited to, a generator, and/or another turbine. Accordingly, a large steam turbine unit may actually include several turbines that are co-axially coupled to the same shaft 14. Such a unit may, for example, include a high pressure turbine coupled to an intermediate-pressure turbine, which is in turn coupled to a low pressure turbine.
The steam turbine 10 shown in
With reference to
During operation, air at atmospheric pressure is compressed by a compressor and delivered to a combustion stage. In the combustion stage (represented by combustors 124), the air leaving the compressor is heated by adding fuel to the air and burning the resulting air/fuel mixture. The gas flow resulting from combustion of fuel in the combustion stage then expands through the turbine 110, delivering some of its energy to drive the turbine 110 and produce mechanical power. To produce driving torque, turbine 110 consists of one or more stages. Each stage includes a row of vanes 122 and a row of rotating blades 120 mounted on a rotor wheel 118. Vanes 122 direct incoming gas from the combustion stage onto blades 120. This drives rotation of the rotor wheel 118, and as a result, shaft 114, producing mechanical power.
The following description specifically references blade 20, but is equally applicable to the blade 120. Turning to
A part-span shroud 48 is attached at an intermediate section of the airfoil portion 32 between the root section 34 and the tip 38. In the exemplary embodiment, part-span shroud sections 50, 52 are located, respectively, on the suction side 44 and pressure side 46 of the airfoil portion 32. In the exemplary embodiment illustrated in
The blade stiffness and damping characteristics are improved as the part-span shrouds contact each other during untwisting of the blade. The plurality of blades 20 thus behave as a single, continuously coupled structure that exhibits improved stiffness and dampening characteristics when compared to a discrete and uncoupled design. Blades 20 also exhibit reduced vibratory stresses.
The tear-drop shaped part-span shroud described above is located substantially midway along the radial length of the airfoil but could be located anywhere between about 40% or 80% of the radial height of the airfoil portion as measured from the root section of the blade.
In a more specific exemplary embodiment, the maximum thickness of the part-span shroud is located at 31% of the length of the chord 84 as measured from the leading edge 82, as shown in
In another exemplary embodiment, the maximum thickness is located at 36% of the length of the chord 84 as measured from the leading edge 82, as shown in
In still another exemplary embodiment, the maximum thickness is located at 37% of the length of the chord 84 as measured from the leading edge 82, as shown in
It will be appreciated that the invention also contemplates geometric scaling of the part-span shroud profiles defined in the above Tables.
It will also be appreciated that for extended length airfoils, the part-span shrouds described herein may be used in combination with conventional airfoil tip shrouds located at the radially-outer tips 38 (
The blade 20 and part-span shroud 80 described above may be used in a variety of turbomachine environments. For example, blades having part-span shrouds 80 as described in connection with
While various embodiments are described herein, it will be appreciated from the specification that various combinations of elements, variations or improvements therein may be made by those skilled in the art, and are within the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims
1. A rotatable blade for a turbomachine comprising:
- an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end;
- a root section affixed to the radially-inner end of the airfoil portion; and
- a substantially tear-drop shaped part-span shroud located on the airfoil portion between the root section and the radially outer end, wherein said part-span shroud is provided with a cross-sectional shape having a maximum thickness located within 20 to 40% of a chord length extending from a leading edge of said part-span shroud to a trailing edge of said part-span shroud, as measured from said leading edge of said part-span shroud.
2. The rotatable blade of claim 1, wherein said maximum thickness is located at about 30% of said chord length.
3. The rotatable blade of claim 1, wherein said said maximum thickness is located between 31% and 37% of said chord length.
4. The rotatable blade of claim 1, wherein said maximum thickness is located at 31% of said chord length and wherein said part-span shroud has a profile defined by the X-Y coordinates set forth in Table I.
5. The rotatable blade of claim 1, wherein said maximum thickness is located at 36% of said chord length and wherein said part-span shroud has a profile defined by the X-Y coordinates set forth in Table II.
6. The rotatable blade of claim 1, wherein said maximum thickness is located at 37% of said chord length and wherein said part-span shroud has a profile defined by the X-Y coordinates set forth in Table III.
7. The rotatable blade of claim 1 wherein the part-span shroud is located substantially midway along a radial length of the airfoil portion.
8. The rotatable blade of claim 1 wherein the rotating blade operates as one of:
- a front stage blade in a compressor,
- a latter stage blade in a gas turbine, or
- a low pressure section blade in a steam turbine.
9. The rotatable blade of claim 1 wherein part-span shrouds on respective pressure and suction sides of adjacent ones of said blades at least partially engage along adjacent, substantially Z-shaped contact surfaces.
10. The rotatable blade of claim 1 wherein part-span shrouds on respective pressure and suction sides of adjacent ones of said blades have substantially-straight contact surfaces.
11. A turbomachine comprising:
- a rotor rotatably mounted within a stator, the rotor including:
- a shaft;
- at least one rotor wheel mounted on the shaft, each of the at least one rotor wheels including a plurality of radially outwardly extending blades mounted thereon; and
- wherein each blade includes an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end, a pressure side and a suction side; a root section at the radially-inner end of said airfoil portion; and a part-span shroud located on said airfoil portion between said root section and said radially outer end, on said pressure side and said suction side, wherein said part-span shroud is provided with a substantially tear-drop cross-sectional shape having a maximum thickness located within 20 to 40% of a chord length extending between a leading edge of said part-span shroud and a trailing edge of said part-span shroud, as measured from said leading edge of said part-span shroud.
12. The turbomachine of claim 11 wherein said maximum thickness is located at 31% of said chord length and wherein said part-span shroud has a profile defined by the X-Y coordinates set forth in Table I.
13. The turbomachine of claim 11, wherein said maximum thickness is located at 36% of said chord length and wherein said part-span shroud has a profile defined by the X-Y coordinates set forth in Table II.
14. The turbomachine of claim 11, wherein said maximum thickness is located at 37% of said chord length and wherein said part-span shroud has a profile defined by the X-Y coordinates set forth in Table III.
15. The turbomachine of claim 11, wherein said blade operates as one of:
- a front stage blade in a compressor,
- a latter stage blade in a gas turbine, or
- a low pressure section blade in a steam turbine.
16. The turbomachine of claim 11 wherein said part-span shroud is located substantially midway along a radial length of said airfoil portion.
17. A turbomachine comprising:
- a rotor rotatably mounted within a stator, the rotor including:
- a shaft;
- at least one rotor wheel mounted on the shaft, each of the at least one rotor wheels including a plurality of radially outwardly extending blades mounted thereon; and
- wherein each blade includes an airfoil portion having a leading edge and a trailing edge, a radially-inner end and a radially-outer end, a pressure side and a suction side; a root section at the radially-inner end of said airfoil portion; and a part-span shroud located on said airfoil portion between said root section and said radially outer end, on said pressure side and said suction side, wherein said part-span shroud is provided with a substantially tear-drop cross-sectional shape having a maximum thickness located at 31%, 36% or 37% of a chord length extending between a leading edge of said part-span shroud and a trailing edge of said part-span shroud, as measured from said leading edge of said part-span shroud; and wherein said part-span shroud is disposed on the airfoil portion between about 40% to 80% of a radial height of said airfoil portion as measured from the root section of the blade.
18. The turbomachine of claim 17 wherein said part-span shroud has a profile defined by the X-Y coordinates as set forth in any one of Tables respectively, or by geometric scaling of said coordinates.
19. The turbomachine of claim 17 wherein part-span shrouds on respective pressure and suction sides of adjacent ones of said blades at least partially engage along adjacent, substantially straight or Z-shaped contact surfaces.
20. The turbomachine of claim 17 wherein said part-span shroud is located substantially midway along said radial height of said airfoil portion.
Type: Application
Filed: Nov 30, 2012
Publication Date: Jun 5, 2014
Applicant: General Electric Company (Bangalore)
Inventor: Rohit CHOUHAN (Bangalore)
Application Number: 13/691,478
International Classification: F01D 5/22 (20060101);