US20130209216A1 - Turbomachine including flow improvement system - Google Patents
Turbomachine including flow improvement system Download PDFInfo
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- US20130209216A1 US20130209216A1 US13/369,843 US201213369843A US2013209216A1 US 20130209216 A1 US20130209216 A1 US 20130209216A1 US 201213369843 A US201213369843 A US 201213369843A US 2013209216 A1 US2013209216 A1 US 2013209216A1
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- airfoil members
- stage
- turbomachine
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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
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- turbomachines include a compressor portion linked to a turbine portion through a common compressor/turbine shaft or rotor and a combustor assembly.
- the compressor portion guides a compressed air flow through a number of sequential stages toward the combustor assembly.
- the compressed air flow mixes with a fuel to form a combustible mixture.
- the combustible mixture is combusted in the combustor assembly to form hot gases.
- the hot gases are guided to the turbine portion through a transition piece.
- the hot gases expand through the turbine creating work that is output, for example, to power a generator, a pump, or to provide power to an aircraft.
- a portion of the compressed airflow is passed through the turbine portion for cooling purposes.
- a method of improving flow in a turbomachine includes guiding a fluid flow across a first turbomachine stage including a first plurality of airfoil members and a second plurality of airfoil members, and guiding the fluid flow across a second turbomachine stage having a third plurality of airfoil members circumferentially off-set relative to the first plurality of airfoil members and a fourth plurality of airfoil members circumferentially off-set relative to the second plurality of airfoil members to improve flow characteristics along the flow path.
- compressor portion 4 is mechanically linked to turbine portion 6 through a common compressor/turbine shaft 12 .
- Compressor portion 4 includes a housing 13 that encases a plurality of compressor stages 14 that extend along a fluid path 16 .
- compressor portion 4 includes a first compressor stage 20 , a second compressor stage 21 , and a third compressor stage 22 .
- Turbine portion 6 includes a housing 23 that encases a plurality of stages 24 that extend along a fluid path 25 .
- the plurality of turbine stages 24 of turbine portion 6 includes a first turbine stage 26 , a second turbine stage 27 and a third turbine stage 28 .
- the number of stages in compressor portion 4 and turbine portion 6 could vary.
- each of the second plurality of rotating airfoil members 36 includes a leading edge 52 and a trailing edge 53 that are joined by a suction side 55 and a pressure side 56 .
- each of the second plurality of stationary airfoil members 39 includes a leading edge 60 and a trailing edge 62 that are joined by a suction side 63 and a pressure side 64 .
- Second plurality of stationary airfoil members 39 are spaced one from another to form a plurality of second stage nozzle passages, one of which is indicated at 66 .
- third plurality of rotating airfoil members 43 include a leading edge 70 and a trailing edge 71 that are joined by a suction side 73 and a pressure side 74 .
- Third plurality of stationary airfoil members 46 include a leading edge 79 and a trailing edge 80 that are joined by a suction side 82 and a pressure side 83 .
- Third plurality of stationary airfoil members 46 are spaced one from another to establish a plurality of third stage nozzle passages, one of which is indicated at 85 .
- turbomachine 2 includes a flow improvement system that takes the form of a multistage clocking arrangement 230 .
- Multi-stage clocking arrangement 230 establishes a predetermined circumferential off-set or clocking of each of the plurality of stationary airfoil members 136 of second turbine stage 27 relative to corresponding ones of each of the plurality of stationary airfoil member 143 of third turbine state 28 by a first margin 200 .
- multi-stage clocking system 230 establishes a predetermined circumferential off-set or clocking of each of the plurality of rotating airfoil 139 of second turbine stage 27 relative to corresponding ones of the rotating airfoil member 146 of third turbine state 28 by a second margin 210 .
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
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- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A turbomachine includes a housing including a fluid path, and a first stage arranged within the housing. The first stage includes a first plurality of airfoil members and a second plurality of airfoil members. A second stage is arranged within the housing relative to the first stage. The second stage includes a third plurality of airfoil members and a fourth plurality of airfoil members. A flow improvement system is associated with each of the first and second stages. The flow improvement system establishes a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members. The predetermined clocking is configured and disposed to improve flow characteristics along the flow path.
Description
- The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a turbomachine including a flow improvement system.
- Many turbomachines include a compressor portion linked to a turbine portion through a common compressor/turbine shaft or rotor and a combustor assembly. The compressor portion guides a compressed air flow through a number of sequential stages toward the combustor assembly. In the combustor assembly, the compressed air flow mixes with a fuel to form a combustible mixture. The combustible mixture is combusted in the combustor assembly to form hot gases. The hot gases are guided to the turbine portion through a transition piece. The hot gases expand through the turbine creating work that is output, for example, to power a generator, a pump, or to provide power to an aircraft. In addition to providing compressed air for combustion, a portion of the compressed airflow is passed through the turbine portion for cooling purposes.
- In many cases, the compressor portion and/or the turbine portion will include an equal number of blades located in successive stationary or rotating rows. In such cases, a circumferential angular spacing between blades is the same in each of the successive rows. Generally, the circumferential spacing results in alignment of blades in the stationary rows and an alignment of blades in the rotating rows. This alignment creates various aerodynamic performance issues and/or thermal environment issues of a flow passing along a flow path of the compressor portion and/or the turbine portion. Manufacturers have clocked or circumferentially off-set adjacent rows of blades in the rotating rows or adjacent rows of blades in the stationary rows to control flow and influence aerodynamic performance and/or thermal environment.
- In the compressor portion, air is drawn in through an intake and passed through the number of sequential stages. Each of the sequential stages includes a plurality of stators or nozzles that guides the air toward a plurality of rotating buckets or blades. The rotating blades force the airflow along the compressor to achieve a desired pressure increase. An interaction pattern, resulting from the air passing across stationary and rotating components, develops at each stage. Above cut-off, perturbations from the interaction coalesce to produce a spinning wave. In some cases, the spinning wave may propagate downstream through the compressor and may enter the combustor assembly. The spinning wave may also propagate upstream. In other cases, the spinning wave may form in a turbine portion and either propagates upstream or downstream along a turbine portion gas path. The development and propagation of the spinning wave can create undesirable unsteady pressure patterns as well as lead to the development of unwanted noise from the compressor portion.
- According to one aspect of the exemplary embodiment, a turbomachine includes a housing including a fluid path, and a first stage arranged within the housing. The first stage includes a first plurality of airfoil members and a second plurality of airfoil members positioned along the fluid path. A second stage is arranged within the housing relative to the first stage. The second stage includes a third plurality of airfoil members and a fourth plurality of airfoil members positioned along the fluid path. A flow improvement system is associated with each of the first and second stages. The flow improvement system establishes a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members. The predetermined clocking is configured and disposed to improve flow characteristics along the flow path.
- According to another aspect of the exemplary embodiment, a turbomachine includes a housing including a fluid path, and a first stage arranged within the housing. The first stage includes a first plurality of airfoil members positioned along the fluid path. A second stage is arranged within the housing relative to the first stage. The second stage includes a second plurality of airfoil members positioned along the fluid path. A flow improvement system is associated with each of the first and second stages. The flow improvement system establishes a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the second plurality of airfoil members. The predetermined clocking is configured and disposed to set up a spinning wave from the second stage that is configured and disposed to interfere with another spinning wave from the first stage.
- According to yet another aspect of the exemplary embodiment, a method of improving flow in a turbomachine includes guiding a fluid flow across a first turbomachine stage including a first plurality of airfoil members and a second plurality of airfoil members, and guiding the fluid flow across a second turbomachine stage having a third plurality of airfoil members circumferentially off-set relative to the first plurality of airfoil members and a fourth plurality of airfoil members circumferentially off-set relative to the second plurality of airfoil members to improve flow characteristics along the flow path.
- According to still another aspect of the exemplary embodiment, a turbomachine includes a housing including a fluid path, and a first stage arranged within the housing. The first stage includes a first plurality of airfoil members and a second plurality of airfoil members positioned along the fluid path. A second stage is arranged within the housing relative to the first stage. The second stage includes a third plurality of airfoil members and a fourth plurality of airfoil members positioned along the fluid path. A flow improvement system is associated with each of the first and second stages. The flow improvement system establishes a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members. The predetermined clocking is configured and disposed to improve flow characteristics along the fluid path and to set up a spinning wave from the second stage that is configured and disposed to interfere with another spinning wave from the first stage.
- These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
- The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
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FIG. 1 is schematic diagram of a turbomachine including a flow improvement system in accordance with an exemplary embodiment; -
FIG. 2 is a schematic representation of a plurality of airfoil members of a compressor portion of the turbomachine ofFIG. 1 in accordance with an exemplary embodiment; -
FIG. 3 is a schematic representation of a plurality of airfoil members of a turbine portion of the turbomachine ofFIG. 1 in accordance with the exemplary embodiment. - The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
- With reference to
FIG. 1 , a turbomachine constructed in accordance with an exemplary embodiment is illustrated generally at 2.Turbomachine 2 includes acompressor portion 4 fluidly connected to aturbine portion 6. Acombustor assembly 8 also fluidly connectscompressor portion 4 andturbine portion 6.Combustor assembly 8 includes a plurality of combustors, one of which is shown at 10, arranged in a can-annular array aboutturbomachine 2. The number and arrangement of combustors can vary. - As shown,
compressor portion 4 is mechanically linked toturbine portion 6 through a common compressor/turbine shaft 12.Compressor portion 4 includes ahousing 13 that encases a plurality ofcompressor stages 14 that extend along afluid path 16. In the exemplary embodiment shown,compressor portion 4 includes afirst compressor stage 20, asecond compressor stage 21, and athird compressor stage 22.Turbine portion 6 includes ahousing 23 that encases a plurality ofstages 24 that extend along afluid path 25. In the exemplary embodiment shown, the plurality ofturbine stages 24 ofturbine portion 6 includes afirst turbine stage 26, asecond turbine stage 27 and athird turbine stage 28. Of course it should be understood that the number of stages incompressor portion 4 andturbine portion 6 could vary. - With this arrangement, air passing into a compressor intake (not separately labeled) flows along
fluid path 16 and is compressed through compressor stages 20-22 to form compressed air. A first portion of the compressed air flows intocombustor assembly 8, mixes with a combustible fluid, and is then combusted to form combustion gases. The combustion gases expand through turbine stages 26-28 alongfluid path 25 ofturbine portion 6 creating work that is output fromturbomachine 2. A second portion of the compressed air passes throughturbine portion 6 as a cooling fluid. -
First compressor stage 20 includes a plurality of rotatingairfoil members 29. Rotatingairfoil members 29 take the form of blades orbuckets 30 that are coupled to common compressor/turbine shaft 12 through a first stage rotor (not shown).First compressor stage 20 also includes a plurality ofstationary airfoil members 32.Stationary airfoil members 32 take the form of vanes ornozzles 33 fixedly mounted relative tocompressor housing 13.Nozzles 33 guide the airflow towardsecond compressor stage 21. Accordingly,second compressor stage 21 includes a plurality of rotatingairfoil members 36. Rotatingairfoil members 36 take the form of blades orbuckets 37 that are coupled to common compressor/turbine shaft 12 through a second stage rotor (not shown).Second compressor stage 21 also includes a plurality ofstationary airfoil members 39.Stationary airfoil members 39 take the form of vanes ornozzles 40 fixedly mounted relative tocompressor housing 13.Nozzles 40 direct the airflow towardthird compressor stage 22.Third compressor stage 22 includes a plurality of rotatingairfoil members 43. Rotatingairfoil members 43 take the form of blades orbuckets 44 that are coupled to common compressor/turbine shaft 12 through a third stage rotor (not shown).Third compressor stage 22 also includes a plurality ofstationary airfoil members 46.Stationary airfoil members 46 take the form of vanes ornozzles 47 fixedly mounted relative tocompressor housing 13.Nozzles 47 guide the airflow toward a subsequent downstream stage (not shown) or towardcombustor assembly 8. - Reference will now be made to
FIG. 2 , in describing second and third compressor stages 21 and 22. As shown, each of the second plurality of rotatingairfoil members 36 includes aleading edge 52 and a trailingedge 53 that are joined by asuction side 55 and apressure side 56. Similarly, each of the second plurality ofstationary airfoil members 39 includes aleading edge 60 and a trailingedge 62 that are joined by asuction side 63 and apressure side 64. Second plurality ofstationary airfoil members 39 are spaced one from another to form a plurality of second stage nozzle passages, one of which is indicated at 66. Likewise, third plurality of rotatingairfoil members 43 include aleading edge 70 and a trailingedge 71 that are joined by asuction side 73 and apressure side 74. Third plurality ofstationary airfoil members 46 include aleading edge 79 and a trailingedge 80 that are joined by asuction side 82 and apressure side 83. Third plurality ofstationary airfoil members 46 are spaced one from another to establish a plurality of third stage nozzle passages, one of which is indicated at 85. - In accordance with one aspect of the exemplary embodiment,
turbomachine 2 includes a flow improvement system that takes the form of a spinningwave reduction system 100 that reduces spinning wave mode propagation alongflow path 16. More specifically, an airflow, such as indicated at 104, passes fromfirst stage 20 towardsecond stage 21.Airflow 104 passes across second plurality of rotatingmembers 36 and creates a wake zone (not shown) that leaves trailingedge 53 and flows towardthird stage 22. Afirst spinning wave 107 having a first pressure pattern or spinningwave mode 109 develops alongflow path 16 as a result of interactions between the second plurality of rotatingmembers 36 and the second plurality ofstationary airfoil members 39. The term “spinning wave” should be understood to include a wave having a non-homogenous pressure pattern that develops as a result of interactions between stationary and rotating members. First spinningwave 107 begins to propagate downstream incompressor portion 4. The airflow passing from trailingedge 71 of third plurality of rotatingairfoil members 43 creates a wake zone (not shown) that passes over the third plurality ofstationary airfoil members 46. Asecond spinning wave 113 including a second pressure pattern or spinningwave mode 115 develops alongflow path 16 as a result of interactions between the third plurality of rotatingmembers 43 and the third plurality ofstationary airfoil members 46.Second spinning wave 113 begins to propagate downstream incompressor portion 4. - Spinning
wave reduction system 100 establishes a desired clocking or circumferential offset of the second plurality of rotatingairfoil members 36 relative to the third plurality of rotatingairfoil members 43. As shown, spinningwave reduction system 100 establishes a desired relative positioning such thatfirst spinning wave 107 passes between second and thirdstage nozzle passages second spinning wave 113 passes through thirdstage nozzle passages 85. The particular clocking established by spinningwave reduction system 100 ensures that firstspinning wave mode 109 and secondspinning wave mode 115 destructively interfere one with the other. The destructive interference reduces downstream propagation of spinning wave modes incompressor portion 4. - In further accordance with an exemplary embodiment,
first turbine stage 26 includes a plurality ofstationary airfoil members 129.Stationary airfoil members 129 take the form of vanes ornozzles 130 that are fixedly mounted relative toturbine housing 23.First turbine stage 26 also includes a plurality of rotatingairfoil members 132. Rotatingairfoil members 132 take the form of blades orbuckets 133 that are coupled to common compressor/turbine shaft 12 through a first stage rotor (not shown).Buckets 133 guide the airflow towardsecond turbine stage 27. Accordingly,second turbine stage 27 includes a plurality ofstationary airfoil members 136.Stationary airfoil members 136 take the form of vanes ornozzles 137 fixedly mounted relative toturbine housing 23.Second turbine stage 27 also includes a plurality of rotatingairfoil members 139. Rotatingairfoil members 139 take the form of blades orbuckets 140 that are coupled to common compressor/turbine shaft 12 through a second stage rotor (not shown).Blades 140 direct the airflow towardthird turbine stage 28.Third turbine stage 28 includes a plurality ofstationary airfoil members 143.Stationary airfoil members 143 take the form of vanes ornozzles 144 fixedly mounted relative toturbine housing 23.Third turbine stage 28 also includes a plurality of rotatingairfoil members 146. Rotatingairfoil members 146 take the form of blades orbuckets 147 that are coupled to common compressor/turbine shaft 12 through a third stage rotor (not shown).Blades 147 guide the airflow toward a subsequent downstream stage (not shown) or to an exhaust system also not shown. - Reference will now be made to
FIG. 3 , in describing second and third turbine stages 27 and 28. As shown, each of the second plurality ofstationary airfoil members 136 includes aleading edge 152 and a trailingedge 153 that are joined by asuction side 155 and apressure side 156. Similarly, each of the second plurality of rotatingairfoil members 139 includes aleading edge 160 and a trailingedge 162 that are joined by asuction side 163 and apressure side 164. Likewise, third plurality ofstationary airfoil members 143 include aleading edge 170 and a trailingedge 172 that are joined by asuction side 173 and apressure side 174. Third plurality of rotatingairfoil members 146 include aleading edge 179 and a trailingedge 180 that are joined by asuction side 182 and apressure side 183. - In accordance with another aspect of the exemplary embodiment,
turbomachine 2 includes a flow improvement system that takes the form of amultistage clocking arrangement 230.Multi-stage clocking arrangement 230 establishes a predetermined circumferential off-set or clocking of each of the plurality ofstationary airfoil members 136 ofsecond turbine stage 27 relative to corresponding ones of each of the plurality ofstationary airfoil member 143 ofthird turbine state 28 by afirst margin 200. In addition,multi-stage clocking system 230 establishes a predetermined circumferential off-set or clocking of each of the plurality ofrotating airfoil 139 ofsecond turbine stage 27 relative to corresponding ones of therotating airfoil member 146 ofthird turbine state 28 by asecond margin 210. In accordance with one aspect of the exemplary embodiment, the first margin is substantially identical tosecond margin 210. In accordance with another aspect of the exemplary embodiment,first margin 200 is distinct fromsecond margin 210. In either case,multi-stage clocking system 230 in which the stationary and rotating airfoil members in one stage are clocked relative to corresponding ones of the stationary and rotating airfoil member of the second stage creates a flow path having cleaner propagation of upstream wakes. Cleaner propagation may take the form of reducing secondary flow between turbine blades that may lead to increased overall machine operating characteristics. - At this point it should be understood that the exemplary embodiments provide a system for improving flow within a turbomachine. The exemplary embodiments enhance fluid flow characteristics in a compressor by setting up destructive interactions between spinning wave modes moving along the flow path and in a turbine by setting a predetermined clocking of sequential turbine stages. The reduction of spinning wave mode propagation in the compressor portion leads to improved combustor operation, reduced system dynamics, and enhanced service life for the turbomachine. The exemplary embodiments also establish a particular turbine flow path that leads to cleaner propagation of upstream wakes. Cleaner propagation of upstream wakes leads to a reduction in secondary flows between turbine blades that enhance overall machine operating characteristics.
- It should be understood that while shown in connection with second and third successive stages in the compressor portion, the spinning wave reduction system could be associated with additional compressor stages that are either successive or spaced one from another by additional stages. Moreover, while described as reducing spinning wave propagation in a compressor portion of a turbomachine, the exemplary embodiment can also be employed to reduce spinning wave propagation in a turbine portion of a turbomachine. It should also be understood that in addition to clocking adjacent rows of the plurality of rotating airfoil members, adjacent rows of the plurality of stationary airfoil members may also be clocked one relative to another. It should be understood that clocking may be achieved by axial blade rows having an equal number of airfoil members or blade rows having a different number of airfoil members. For example, clocking may be achieved by employing a blade row or rows having an integer multiple of airfoil members relative to an adjacent blade row.
- Furthermore, the exemplary embodiments include clocking adjacent stages of the turbomachine, such that stators in one stage are clocked relative to stators in an adjacent stage, and rotors in the one stage are clocked relative to rotors in the adjacent stage. Additionally, while described in terms of modifying spinning waves propagating downstream through a compressor portion, the spinning wave reduction system can also be configured to modify spinning waves traveling upstream through the compressor portion.
- While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
Claims (20)
1. A turbomachine comprising:
a housing including a fluid path;
a first stage arranged within the housing, the first stage including a first plurality of airfoil members and a second plurality of airfoil members positioned along the fluid path;
a second stage arranged within the housing relative to the first stage, the second stage including a third plurality of airfoil members and a fourth plurality of airfoil members positioned along the fluid path; and
a flow improvement system associated with each of the first and second stages, the flow improvement system establishing a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members, the predetermined clocking being configured and disposed to improve flow characteristics along the flow path.
2. The turbomachine according to claim 1 , wherein each of the first plurality of airfoil members is circumferentially off-set relative to corresponding ones of each of the third plurality of airfoil members by a first margin.
3. The turbomachine according to claim 2 , wherein each of the second plurality of airfoil members are circumferentially off-set relative to each of the fourth plurality of airfoil members by a second margin.
4. The turbomachine according to claim 3 , wherein the first margin is substantially identical to the second margin.
5. The turbomachine according to claim 1 , wherein the turbomachine constitutes a turbine portion.
6. A turbomachine comprising:
a housing including a fluid path;
a first stage arranged within the housing, the first stage including a first plurality of airfoil members positioned along the fluid path;
a second stage arranged within the housing relative to the first stage, the second stage including a second plurality of airfoil members positioned along the fluid path; and
a flow improvement system associated with each of the first and second stages, the flow improvement system establishing a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the second plurality of airfoil members, the predetermined clocking being configured and disposed to set up a spinning wave from the second stage that is configured and disposed to interfere with another spinning wave from the first stage.
7. The turbomachine according to claim 6 , wherein the first plurality of airfoil members constitute a first plurality of rotating airfoil members and the second plurality of airfoil members constitute a second plurality of rotating airfoil members.
8. The turbomachine according to claim 6 , wherein the first plurality of airfoil members constitutes a first plurality of rotating airfoil members and a first plurality of stationary airfoil members, and the second plurality of airfoil members constitute a second plurality of rotating airfoil members and a second plurality of stationary airfoil members.
9. The turbomachine according to claim 8 , wherein the spinning wave reduction system establishes the predetermined clocking of the second plurality of rotating airfoil members relative to the first plurality of rotating airfoil members.
10. The turbomachine according to claim 8 , wherein the second plurality of stationary airfoil members are spaced one from another to form a plurality of second stage stationary airfoil passages.
11. The turbomachine according to claim 10 , wherein the spinning wave reduction system establishes the predetermined clocking so as to cause the first spinning wave passing from the first plurality of rotating airfoil members to pass through the plurality of second stage stationary airfoil passages and interfere with the second spinning wave passing from the second plurality of rotating airfoil members.
12. The turbomachine according to claim 6 , wherein the turbomachine constitutes a compressor portion.
13. A method of improving flow in a turbomachine, the method comprising:
guiding a fluid flow across a first turbomachine stage including a first plurality of airfoil members and a second plurality of airfoil members; and
guiding the fluid flow across a second turbomachine stage having a third plurality of airfoil members circumferentially off-set relative to the first plurality of airfoil members and a fourth plurality of airfoil members circumferentially off-set relative to the second plurality of airfoil members to improve flow characteristics along the flow path.
14. The method according to claim 13 , wherein guiding the fluid flow across the first plurality of airfoil members includes passing the fluid flow across a plurality of stationary airfoil members.
15. The method of claim 14 , wherein guiding the fluid flow over the second plurality of airfoil members includes passing the first fluid across a plurality of rotating airfoil members arranged downstream of the plurality of stationary airfoil members.
16. The method of claim 13 , wherein passing the fluid flow over the first plurality of airfoil members includes passing the fluid flow over a first turbomachine stage having a first predetermined number of stationary airfoil members and passing the fluid flow over the third plurality of airfoil members includes passing the fluid flow over a second turbomachine stage having a second predetermined number of stationary airfoil members that is identical to the first predetermined number.
17. The method of claim 13 , wherein passing the fluid flow over the first plurality of airfoil members includes passing the fluid flow over a first turbomachine stage having a first predetermined number of stationary airfoil members and passing the fluid flow over the third plurality of airfoil members includes passing the fluid flow over a second turbomachine stage having a second predetermined number of stationary airfoil members that is distinct from the first predetermined number.
18. The method of claim 13 , wherein passing the fluid flow over the second plurality of airfoil members includes passing the fluid flow over a first turbomachine stage having a first predetermined number of rotating airfoil members and passing the fluid flow over the fourth plurality of airfoil members includes passing the fluid flow over a second turbomachine stage having a second predetermined number of rotating airfoil members that is identical to the first predetermined number.
19. The method of claim 13 , wherein passing the fluid flow over the second plurality of airfoil members includes passing the fluid flow over a first turbomachine stage having a first predetermined number of rotating airfoil members and passing the fluid flow over the fourth plurality of airfoil members includes passing the fluid flow over a second turbomachine stage having a second predetermined number of rotating airfoil members that is distinct from the first predetermined number.
20. A turbomachine comprising:
a housing including a fluid path;
a first stage arranged within the housing, the first stage including a first plurality of airfoil members and a second plurality of airfoil members positioned along the fluid path;
a second stage arranged within the housing relative to the first stage, the second stage including a third plurality of airfoil members and a fourth plurality of airfoil members positioned along the fluid path; and
a flow improvement system associated with each of the first and second stages, the flow improvement system establishing a predetermined clocking of each of the first plurality of airfoil members relative to corresponding ones of each of the third plurality of airfoil members, and each of the second plurality of airfoil members relative to each of the fourth plurality of airfoil members, the predetermined clocking being configured and disposed to improve flow characteristics along the fluid path and to set up a spinning wave from the second stage that is configured and disposed to interfere with another spinning wave from the first stage.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
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US13/369,843 US20130209216A1 (en) | 2012-02-09 | 2012-02-09 | Turbomachine including flow improvement system |
EP13154218.5A EP2628898A3 (en) | 2012-02-09 | 2013-02-06 | Turbomachine Including Flow Improvement System |
RU2013105205/06A RU2013105205A (en) | 2012-02-09 | 2013-02-07 | TURBO MACHINE (OPTIONS) AND METHOD FOR OPTIMIZING FLOW IN A TURBO MACHINE |
CN2013100493911A CN103244201A (en) | 2012-02-09 | 2013-02-07 | Turbomachine including flow improvement system |
JP2013021853A JP2013164069A (en) | 2012-02-09 | 2013-02-07 | Turbomachine including flow improvement system |
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US13/369,843 US20130209216A1 (en) | 2012-02-09 | 2012-02-09 | Turbomachine including flow improvement system |
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US20130209216A1 true US20130209216A1 (en) | 2013-08-15 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/369,843 Abandoned US20130209216A1 (en) | 2012-02-09 | 2012-02-09 | Turbomachine including flow improvement system |
Country Status (5)
Country | Link |
---|---|
US (1) | US20130209216A1 (en) |
EP (1) | EP2628898A3 (en) |
JP (1) | JP2013164069A (en) |
CN (1) | CN103244201A (en) |
RU (1) | RU2013105205A (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11021970B2 (en) * | 2019-02-20 | 2021-06-01 | General Electric Company | Turbomachine with alternatingly spaced rotor blades |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5486091A (en) * | 1994-04-19 | 1996-01-23 | United Technologies Corporation | Gas turbine airfoil clocking |
US20020048510A1 (en) * | 2000-10-23 | 2002-04-25 | Fiatavio S.P.A. | Method of positioning turbine stage arrays, particularly for aircraft engines |
US20020057966A1 (en) * | 2000-10-27 | 2002-05-16 | Andreas Fiala | Blade row arrangement for turbo-engines and method of making same |
US6402458B1 (en) * | 2000-08-16 | 2002-06-11 | General Electric Company | Clock turbine airfoil cooling |
US20090155062A1 (en) * | 2007-12-14 | 2009-06-18 | Snecma | Method of designing a multistage turbine for a turbomachine |
US20100166538A1 (en) * | 2008-12-29 | 2010-07-01 | General Electric Company | Turbine airfoil clocking |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4606699A (en) * | 1984-02-06 | 1986-08-19 | General Electric Company | Compressor casing recess |
GB0802309D0 (en) * | 2008-02-08 | 2008-03-12 | Hawkhill Inc Llc 1 | Gas compressor |
-
2012
- 2012-02-09 US US13/369,843 patent/US20130209216A1/en not_active Abandoned
-
2013
- 2013-02-06 EP EP13154218.5A patent/EP2628898A3/en not_active Withdrawn
- 2013-02-07 JP JP2013021853A patent/JP2013164069A/en active Pending
- 2013-02-07 CN CN2013100493911A patent/CN103244201A/en active Pending
- 2013-02-07 RU RU2013105205/06A patent/RU2013105205A/en not_active Application Discontinuation
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5486091A (en) * | 1994-04-19 | 1996-01-23 | United Technologies Corporation | Gas turbine airfoil clocking |
US6402458B1 (en) * | 2000-08-16 | 2002-06-11 | General Electric Company | Clock turbine airfoil cooling |
US20020048510A1 (en) * | 2000-10-23 | 2002-04-25 | Fiatavio S.P.A. | Method of positioning turbine stage arrays, particularly for aircraft engines |
US20020057966A1 (en) * | 2000-10-27 | 2002-05-16 | Andreas Fiala | Blade row arrangement for turbo-engines and method of making same |
US20090155062A1 (en) * | 2007-12-14 | 2009-06-18 | Snecma | Method of designing a multistage turbine for a turbomachine |
US20100166538A1 (en) * | 2008-12-29 | 2010-07-01 | General Electric Company | Turbine airfoil clocking |
Non-Patent Citations (2)
Title |
---|
S. Kamiyoshi and S. Kaji, Application of Airfoil Clocking Technology to Reduction of Multi-Stage Fan Tone, May 2001, American Institute of Aeronautics & Astonautics, AIAA-2001-2149 * |
S. Kamiyoshi and S. Kaji, Tone Noise Reduction of Multi-Stage Fan by Airfoil Clocking, June 2000, American Institute of Aeronautics & Astonautics, AIAA-2000-1992 * |
Also Published As
Publication number | Publication date |
---|---|
JP2013164069A (en) | 2013-08-22 |
EP2628898A3 (en) | 2016-02-17 |
EP2628898A2 (en) | 2013-08-21 |
RU2013105205A (en) | 2014-08-20 |
CN103244201A (en) | 2013-08-14 |
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Legal Events
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AS | Assignment |
Owner name: GENERAL ELECTRIC COMPANY, NEW YORK Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SIMPSON, STANLEY FRANK;SORANNA, FRANCESCO;RANGWALLA, AKIL ABBAS;AND OTHERS;SIGNING DATES FROM 20111129 TO 20111206;REEL/FRAME:027680/0065 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |