EP2304183A2 - Verfahren und vorrichtung zur beeinflussung von sekundärströmungen bei einer turbomaschine - Google Patents
Verfahren und vorrichtung zur beeinflussung von sekundärströmungen bei einer turbomaschineInfo
- Publication number
- EP2304183A2 EP2304183A2 EP09772488A EP09772488A EP2304183A2 EP 2304183 A2 EP2304183 A2 EP 2304183A2 EP 09772488 A EP09772488 A EP 09772488A EP 09772488 A EP09772488 A EP 09772488A EP 2304183 A2 EP2304183 A2 EP 2304183A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- main flow
- passage
- swirl
- flow direction
- hub
- 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- Withdrawn
Links
Classifications
-
- 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
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- 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
- F01D5/145—Means for influencing boundary layers or secondary circulations
Definitions
- the invention relates to an apparatus and method for reducing secondary flows in a passage between two adjacent blades and vanes of a turbomachine, each of the blades extending from a side wall of a hub of the turbomachine, and wherein the passage is traversed by a fluid in a main flow direction ,
- the inflowing fluid is deflected in the main flow direction according to the geometry of the blades.
- the pressure and centrifugal forces acting on a fluid particle are in equilibrium.
- hub side wall and housing side wall form due to friction sidewall boundary layers with low energy fluid.
- a pressure gradient is formed, which leads to a transverse transport of the low-energy fluid of the sidewall boundary layer.
- a compensating counter-rotating flow forms, which forms a secondary vortex with the flow along the hub and housing side wall.
- One known way of influencing and controlling secondary flow phenomena is by exhausting the sidewall and / or blade boundary layers by injecting mass flow at suitable positions in front of or behind the blade row or in the passage. In this case, additional energy must be made available for transporting the extracted or injected mass flow. In the extraction, a mass loss is directly accepted, which consumes the aerodynamic improvements by actively influencing a part again.
- secondary flow in turbomachinery components can passively pass through, for example, boundary fences or additional baffles
- Flow control are influenced, which always means extensive design measures to guide the mass flow. In these methods, great design effort must be operated.
- the boundary layer fences and baffles are exposed to significant forces, reducing life and structural strength. Boundary layer fences require additional components. In addition to an increase in the friction surfaces, the structural limitations arise.
- the invention has for its object to provide a method and apparatus for influencing secondary flows in a passage between two adjacent vanes of a turbomachine to reduce internal losses.
- the method according to the invention is defined by the features of claim 1.
- the device according to the invention is defined by the features of claim 9.
- a stable auxiliary vortex of the fluid flowing through the passage is generated using a vortex channel formed in the hub side wall.
- the swirl duct is not rotationally symmetric with respect to the hub axle, whereby the auxiliary swirl generated is rotated in the passage perpendicular to the main flow direction and opposite to a secondary swirl.
- the auxiliary swirl thus rotates in a plane perpendicular to the main flow direction and its direction of rotation is opposite to that of the secondary vortex.
- the auxiliary swirl is thereby an aerodynamic separator, which counteracts the secondary vortex.
- the auxiliary swirl prevents the mass transport of the fluid to the blade suction side, thereby preventing the interaction of the sidewall and blade boundary layer, their coalescence or the emergence of corner separation.
- the swirl duct is formed in the housing and / or in the hub side wall, extends in the main flow direction and is not rotationally symmetrical with respect to the hub axle. As the fluid flows in the main flow direction along the swirl passage, a stable auxiliary fluid swirl is generated which is rotated perpendicular to the main flow direction and opposite to a secondary swirl.
- the auxiliary vortex and the secondary vortex cancel each other as it flows through the passage.
- the total pressure loss coefficient is reduced by approx. 30%.
- the swirl duct is formed as a concave depression of the hub side wall in the form of a throat, wherein the swirl duct forms a spoiler edge with respect to the main flow direction upstream with the hub side wall and forms a flank on the side facing the adjacent pressure side of a vane.
- the fluid flows through the vortex channel in the main flow direction and is swirled at the trailing edge.
- the trailing edge with the hub side wall forms an angle between 30 ° and 60 °, preferably about 45 °.
- the flank causes the auxiliary swirl to be guided in the main flow direction through the passage, producing a vortex which rotates counter to the direction of the channel vortex.
- the auxiliary vortex and the secondary vortex collide and form a detachment line.
- the auxiliary vortex strikes the secondary vortex in the area of the flank and prevents mass transport in the direction of the suction side due to the secondary vortex.
- the geometric shape, the depth and shape and angle of the trailing edge and the flank are ideally chosen so that the auxiliary vortex rotates with the same intensity and speed as the secondary vortex.
- the auxiliary swirl is transported through the passage in the main flow direction and counteracts the secondary swirl at any point along the detachment line.
- the vortex channel begins in the main flow direction before the beginning of the passage and ends in the main flow direction in the region of the passage end, so that the auxiliary vortex in the region of the blade trailing edge loses intensity and dissipates to avoid interaction with the downstream blade row.
- the tear-off edge can be designed in the form of a fillet radius or as a sharp-edged corner.
- the auxiliary swirl should interact neither with the suction nor with the pressure-side boundary layer of the blades. Such an interaction between the suction side boundary layer of the blade and the auxiliary swirl can be avoided by leaving a sufficient distance between the swirl channel and the guide blade.
- the width of the spinal canal should match the division, i. the distance between two adjacent blades, be scaled.
- the fluid of the incoming sidewall boundary layer rolls up into a stable auxiliary vortex within the throat.
- the main flow then passes this vortex along the correspondingly shaped vortex channel, thus creating the aerodynamic separator at which the transverse transport of the sidewall boundary layer material is inhibited.
- the detachment line is formed due to the two oppositely rotating vortices.
- Figure 1 is a perspective view of an embodiment of the device according to the invention.
- Figure 2 is a plan view from the direction of the arrow II in Figure 1.
- FIG. 1 shows the circumferential surface of the hub of a blade row.
- the blade row can protrude outward from the hub of a stator or protrude inwardly from the surrounding housing of a stator.
- the hub side wall 12 can be seen, from which blades 14 protrude in the radial direction.
- Each of the blades 14 has a convex suction side 16 and the suction side 16 opposite a concave pressure side 18.
- the two adjacent blades 14 form a passage 20, which is flowed through by a fluid in the main flow direction 23 during operation of the turbomachine.
- the main flow direction 23 is shown by the arrow with the reference numeral 22 in Figure 1 and extends from the leading edge 24 of a vane 14 to the rear edge 26th
- a fluid boundary layer forms along the hub side wall 12 in the region of the hub side wall.
- the pressure gradient between the suction side 16 and pressure side 18 of the two blades 14 results in a secondary vortex 28, which rotates counterclockwise in FIG.
- each swirl duct is not rotationally symmetrical with respect to the hub axle and has a spoiler lip 32 at its end located in front of the blade leading edge 24. Behind the tear-off edge 32 takes the depth of the vertebral canal 30 to its lowest point. The lowest point of the swirling channel 30 is preferably located in front of the blade leading edge 24.
- each vertebral canal 30 has an approximately kidney-shaped curved shape except for the tear-off edge 32.
- the curvature of the swirling channel 30 in plan view extends according to the curvature of the blade 14.
- the swirling channel 30 has an elongated curved shape of continuously varying depth and forms a throat with a flank 34 extending in the region of the center of the passage.
- the flank 34 extends along the pressure side of the adjacent blade 14 facing side of the vortex can.
- the slope of the flank 34 is greater than the slope on the opposite, the adjacent suction side 16 facing side of the swirl passage 30.
- the slope of the flank 34 decreases in the main flow direction 23 continuously and ends at the end of the passage in the region of the guide blade trailing edge 26.
- the depth of the swirling channel 30 in the main flow direction first increases rapidly in the region of the spoiler edge, reaches its greatest value in front of the blade leading edge 24 and runs continuously up to the blade trailing edge 26.
- the depth of the swirling channel 30 in the region of the flank 34 first increases rapidly to the lowest point in the region of the center of the swirling channel 30 and then continuously decreases in the direction of the suction side 16 , Between the suction side 16 and the suction side 16 facing side of the swirl passage 30 remains in the rear region of the blade 14 a distance.
- auxiliary swirl 36 When the fluid flows in the main flow direction 23, the fluid flow drops down over the tear-off edge 32 into the throat of the swirling channel 30 and forms an auxiliary swirl 36 along the tear-off edge 32 and along the flank 34, which, as in FIG shown rotated counterclockwise in the direction of rotation of the secondary vortex 28 (channel vortex).
- the auxiliary swirl 36 is transported along the flank 34 and forms a detachment line 22 along the auxiliary swirl 36 in the region of the center of the passage 20, ie in the region between two adjacent blades 14, together with the secondary swirl 28 hits the secondary vortex 28.
- auxiliary helix 36 and secondary vortex 28 meet, they counteract each other so that an aerodynamic separator is formed by auxiliary vortex 36, which prevents secondary flow 28 from causing mass flow in the direction of suction side 16.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200810031789 DE102008031789A1 (de) | 2008-07-04 | 2008-07-04 | Verfahren und Vorrichtung zur Beeinflussung von Sekundärströmungen bei einer Turbomaschine |
PCT/EP2009/058290 WO2010000788A2 (de) | 2008-07-04 | 2009-07-01 | Verfahren und vorrichtung zur beeinflussung von sekundärströmungen bei einer turbomaschine |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2304183A2 true EP2304183A2 (de) | 2011-04-06 |
Family
ID=41396763
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09772488A Withdrawn EP2304183A2 (de) | 2008-07-04 | 2009-07-01 | Verfahren und vorrichtung zur beeinflussung von sekundärströmungen bei einer turbomaschine |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP2304183A2 (de) |
DE (1) | DE102008031789A1 (de) |
WO (1) | WO2010000788A2 (de) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011008812A1 (de) | 2011-01-19 | 2012-07-19 | Mtu Aero Engines Gmbh | Zwischengehäuse |
EP2806103B1 (de) * | 2013-05-24 | 2019-07-17 | MTU Aero Engines AG | Schaufelgitter und Strömungsmaschine |
FR3106627B1 (fr) * | 2020-01-24 | 2023-03-17 | Safran Aircraft Engines | Basculement en vagues aux entrefers rotor-stator dans un compresseur de turbomachine |
CN111931306A (zh) * | 2020-07-31 | 2020-11-13 | 上海交通大学四川研究院 | 基于辅助涡对影响主涡对相互作用进程的调控方法及系统 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1602965A (de) * | 1968-08-16 | 1971-03-01 | ||
JPS5267404A (en) * | 1975-12-01 | 1977-06-03 | Hitachi Ltd | Blades structure |
JPS5688901A (en) * | 1979-12-19 | 1981-07-18 | Hitachi Ltd | Staged turbine construction |
DE3023466C2 (de) * | 1980-06-24 | 1982-11-25 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Einrichtung zur Verminderung von Sekundärströmungsverlusten in einem beschaufelten Strömungskanal |
EP0943784A1 (de) * | 1998-03-19 | 1999-09-22 | Asea Brown Boveri AG | Konturierter Kanal einer axialen Strömungsmaschine |
US6561761B1 (en) * | 2000-02-18 | 2003-05-13 | General Electric Company | Fluted compressor flowpath |
US6669445B2 (en) * | 2002-03-07 | 2003-12-30 | United Technologies Corporation | Endwall shape for use in turbomachinery |
EP1760257B1 (de) * | 2004-09-24 | 2012-12-26 | IHI Corporation | Wandform einer axialmaschine und gasturbinenmotor |
JP5283855B2 (ja) * | 2007-03-29 | 2013-09-04 | 株式会社Ihi | ターボ機械の壁、及びターボ機械 |
FR2926856B1 (fr) * | 2008-01-30 | 2013-03-29 | Snecma | Compresseur de turboreacteur |
DE102008021053A1 (de) * | 2008-04-26 | 2009-10-29 | Mtu Aero Engines Gmbh | Nachgeformter Strömungspfad einer Axialströmungsmaschine zur Verringerung von Sekundärströmung |
-
2008
- 2008-07-04 DE DE200810031789 patent/DE102008031789A1/de not_active Withdrawn
-
2009
- 2009-07-01 WO PCT/EP2009/058290 patent/WO2010000788A2/de active Application Filing
- 2009-07-01 EP EP09772488A patent/EP2304183A2/de not_active Withdrawn
Non-Patent Citations (1)
Title |
---|
See references of WO2010000788A3 * |
Also Published As
Publication number | Publication date |
---|---|
WO2010000788A3 (de) | 2011-01-20 |
DE102008031789A1 (de) | 2010-01-07 |
WO2010000788A2 (de) | 2010-01-07 |
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Legal Events
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AX | Request for extension of the european patent |
Extension state: AL BA RS |
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RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: NICKE, EBERHARD Inventor name: DORFNER, CHRISTIAN |
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18D | Application deemed to be withdrawn |
Effective date: 20160712 |