EP3379033A1 - Systeme und verfahren zur minimierung eines einfallswinkels zwischen einer anzahl von stromlinien in einem nicht gestörten strömungsfeld durch änderung eines neigungswinkels einer sehnenlinie eines dämpfers - Google Patents
Systeme und verfahren zur minimierung eines einfallswinkels zwischen einer anzahl von stromlinien in einem nicht gestörten strömungsfeld durch änderung eines neigungswinkels einer sehnenlinie eines dämpfers Download PDFInfo
- Publication number
- EP3379033A1 EP3379033A1 EP17161833.3A EP17161833A EP3379033A1 EP 3379033 A1 EP3379033 A1 EP 3379033A1 EP 17161833 A EP17161833 A EP 17161833A EP 3379033 A1 EP3379033 A1 EP 3379033A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- snubber
- blade
- local
- chord line
- streamlines
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
Definitions
- the disclosure relates generally to gas and/or steam turbine engines and more particularly relate to systems and methods for minimizing an incidence angle between a number of streamlines in a not disturbed flow field by varying an inclination angle of a chord line of a snubber.
- the incidence angle between the streamlines of a not disturbed flow field between adjacent blades and the snubber radial inclination angle (snubber chord line or principal axis stagger angle) and also the snubber surface are generally aerodynamic loss amplifiers. Snubbers that are not aligned are prone to thickened boundary layers and/or flow separation downstream thereof at the snubber trailing edge and on the surrounding blade surfaces. Secondary flow may be formed in the separation and wake zones. The above discussed incidence angle on the snubber may generate an undesirable lift on the snubber and lift related secondary flow.
- the flow yaw angle variation from the pressure to suction side of the adjacent blades needs to be considered and the geometry accordingly adapted in the pitch-wise direction.
- a system including a first blade, a second blade, and a snubber disposed between a pressure side of the first blade and a suction side of the second blade.
- An inclination angle of a chord line of the snubber may be varied from the pressure side of the first blade to the suction side of the second blade to minimize an incidence angle between a number of streamlines in a not disturbed flow field and the inclination angle of the chord line.
- a snubber disposed between a pressure side of a first blade and a suction side of a second blade.
- the snubber includes a leading edge, a trailing edge, and a chord line.
- An inclination angle of a chord line of the snubber may be varied from the pressure side of the first blade to the suction side of the second blade to minimize an incidence angle between a number of streamlines in a not disturbed flow field and the inclination angle of the chord line.
- a method includes positioning a snubber between a pressure side of a first blade and a suction side of a second blade.
- the method also includes varying an inclination angle of a chord line of the snubber from the pressure side of the first blade to the suction side of the second blade to minimize an incidence angle between a plurality of streamlines in a not disturbed flow field and the inclination angle of the chord line.
- FIG. 1 depicts a schematic view of gas turbine engine 10 as may be used herein.
- the gas turbine engine 10 may include a compressor 15.
- the compressor 15 compresses an incoming flow of air 20.
- the compressor 15 delivers the compressed flow of air 20 to a combustor 25.
- the combustor 25 mixes the compressed flow of air 20 with a compressed flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35.
- the gas turbine engine 10 may include any number of combustors 25.
- the flow of combustion gases 35 is in turn delivered to a turbine 40.
- the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
- the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
- the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
- the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
- the gas turbine engine 10 may have different configurations and may use other types of components.
- Other types of gas turbine engines also may be used herein.
- Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
- a steam or vapor turbine may also be used herein in addition to or in lieu of the gas turbine engine.
- the steam/vapor turbine may be fed by any vapor generator (boiler, heat exchanger, or any suitable device for this purpose).
- the turbine may use any liquid in a vapor state, but is not restricted thereto. Any liquid-vapor mixtures, gases, or liquids are similarly applicable.
- Other types of steam/vapor turbine engines also may be used herein.
- Multiple steam/vapor turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
- a heating device may replace the compressor 15 and the combustor 25.
- FIGS. 2 and 3 depict a snubber 100 disposed between a first blade 102 and a second blade 104 in a gas turbine engine.
- the second blade 104 has been omitted in FIG. 3 for clarity.
- the snubber 100 may be disposed between blades in a compressor or turbine.
- the snubber 100 may be referred to as a part span connector.
- the snubber 100 may be attached to the pressure side 106 of the first blade 102 and the suction side 108 of the second blade 104.
- the snubber 100 may be attached to the pressure side 106 of the first blade 102 and/or the suction side 108 of the second blade 104 by fillets 109.
- the snubber 100 may include a leading edge 111 and a trailing edge 113.
- the snubber 100 may be an airfoil or the like.
- the snubber 100 may be any size, shape, or configuration.
- FIGS. 2 and 3 A number of streamlines 110 are depicted in FIGS. 2 and 3 .
- the streamlines 110 represent streamlines in a not disturbed flow field (i.e., streamlines between the first blade 102 and the second blade 104 if the snubber 100 was omitted).
- an incidence angle between the streamlines 110 in the not disturbed flow field may be minimized by varying an inclination angle ( ⁇ ) of a chord line 112 of the snubber 100 from the pressure side 106 of the first blade 102 to the suction side 108 of the second blade 104. That is, the inclination angle of chord line 112 may be varied between the pressure side 106 of the first blade 102 and the suction side 108 of the second blade 104.
- the incidence angle includes a region about the fillets 109.
- ⁇ ss depicts the inclination angle of the snubber 100 at the suction side 108 of the second blade 104
- yps depicts the inclination angle of the snubber 100 at the pressure side 106 of the first blade 102
- ⁇ k depicts the inclination angle of the snubber 100 at the center of the snubber 100 and/or any intermediate position between the pressure 106 side of the first blade 102 and suction 108 side of the second blade 104 .
- ⁇ ss, ⁇ ps, and/or ⁇ k may be the same or may vary depending on the respective local streamlines 110. In this manner, the inclination angle of the chord line 112 may vary at any point across the width of the snubber 100 in order to minimize the incidence angle between the chord line 112 and the streamlines 110 across the width of the snubber 100.
- the inclination angle of chord line 112 may be varied such that the incidence angle may be less than about 20 degrees along the span of the snubber 100. In other instances, the incidence angle may be about 15 degrees.
- the inclination angle may be calculated between a slope of a local streamline 100 and a relevant local slope of the chord line 112.
- FIG. 4 is a three dimensional flow vector and projection to the meridional plane.
- FIG. 4 is a three dimensional flow vector and projection to the meridional plane.
- FIG. 5 depicts a cross section of the snubber 100.
- S is the curve length along the boundary of the snubber's cross section starting at the leading edge 111 (e.g., minimum x-coordinate).
- leading edge 111 is the minimum x-coordinate
- trailing edge 113 is the maximum x-coordinate.
- ⁇ i is the delta of the flow yaw angle and the snubber surface inclination at any selected position "i.”
- a deviation of a local chord line 112 to a local radial flow angle of a local streamline 110 may be equal to or less than about 20 degrees for all positions (i) along the snubber surface S. In other instances, a deviation of a local surface S of the snubber to a local radial flow angle of a local streamline 110 may be equal to or less than about 15 degrees for all positions (i) along a first 20% of the snubber surface S from the leading edge 111.
- a deviation of a local surface of the snubber to a local radial flow angle of a local streamline 110 may be equal to or less than about 10 degrees for all positions (i) along a remaining 80% of the snubber surface S.
- the pitch-wise flow aligned snubber/winglet design disclosed herein achieves minimum flow incidence and allows 20-60% loss reduction compared to typical prior art designs. Customers expect safe and endurable machine operation with maximum achievable performance (power output) for a given turbine size.
- the size of a turbine is often characterized by exit area of rotating blade of the last turbine stage. Based on the blade design (and especially for very long blades), part-span-connectors (snubbers) are commonly use.
- the flow aligned part-span-connector (snubber) design disclosed herein reduces the related performance losses for stiff snubbers (mainly used for mechanical stiffening) but is also applicable for winglet designs targeting to introduce additional damping on any blade movement/vibration. This application can be applied to new designs and/or to retrofit previous geometries.
- the mentioned performance improvement is not restricted to turbine blades but also applies to compressor blades and any devices of similar intent.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17161833.3A EP3379033A1 (de) | 2017-03-20 | 2017-03-20 | Systeme und verfahren zur minimierung eines einfallswinkels zwischen einer anzahl von stromlinien in einem nicht gestörten strömungsfeld durch änderung eines neigungswinkels einer sehnenlinie eines dämpfers |
PCT/US2018/016910 WO2018175003A1 (en) | 2017-03-20 | 2018-02-05 | Snubber with minimized incidence angle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17161833.3A EP3379033A1 (de) | 2017-03-20 | 2017-03-20 | Systeme und verfahren zur minimierung eines einfallswinkels zwischen einer anzahl von stromlinien in einem nicht gestörten strömungsfeld durch änderung eines neigungswinkels einer sehnenlinie eines dämpfers |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3379033A1 true EP3379033A1 (de) | 2018-09-26 |
Family
ID=58398051
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17161833.3A Withdrawn EP3379033A1 (de) | 2017-03-20 | 2017-03-20 | Systeme und verfahren zur minimierung eines einfallswinkels zwischen einer anzahl von stromlinien in einem nicht gestörten strömungsfeld durch änderung eines neigungswinkels einer sehnenlinie eines dämpfers |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP3379033A1 (de) |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5460488A (en) * | 1994-06-14 | 1995-10-24 | United Technologies Corporation | Shrouded fan blade for a turbine engine |
EP2009241A2 (de) * | 2007-06-27 | 2008-12-31 | Kabushiki Kaisha Toshiba | Mit einander verbundene Schaufeln einer Dampfturbine |
EP2339115A2 (de) * | 2009-12-28 | 2011-06-29 | Kabushiki Kaisha Toshiba | Turbinenrotorbaugruppe und Dampfturbine |
EP2738351A1 (de) * | 2012-11-30 | 2014-06-04 | General Electric Company | Rotorschaufel mit einem Tränenförmig geformten Dämpfer in einer Teilhöhe des Schaufelblatts |
-
2017
- 2017-03-20 EP EP17161833.3A patent/EP3379033A1/de not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5460488A (en) * | 1994-06-14 | 1995-10-24 | United Technologies Corporation | Shrouded fan blade for a turbine engine |
EP2009241A2 (de) * | 2007-06-27 | 2008-12-31 | Kabushiki Kaisha Toshiba | Mit einander verbundene Schaufeln einer Dampfturbine |
EP2339115A2 (de) * | 2009-12-28 | 2011-06-29 | Kabushiki Kaisha Toshiba | Turbinenrotorbaugruppe und Dampfturbine |
EP2738351A1 (de) * | 2012-11-30 | 2014-06-04 | General Electric Company | Rotorschaufel mit einem Tränenförmig geformten Dämpfer in einer Teilhöhe des Schaufelblatts |
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