EP2394028A1 - Abdichtvorrichtung an dem schaufelschaft einer rotorstufe einer axialen strömungsmaschine - Google Patents
Abdichtvorrichtung an dem schaufelschaft einer rotorstufe einer axialen strömungsmaschineInfo
- Publication number
- EP2394028A1 EP2394028A1 EP10710168A EP10710168A EP2394028A1 EP 2394028 A1 EP2394028 A1 EP 2394028A1 EP 10710168 A EP10710168 A EP 10710168A EP 10710168 A EP10710168 A EP 10710168A EP 2394028 A1 EP2394028 A1 EP 2394028A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- sealing device
- rotor
- bulkheads
- bottom plates
- 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.)
- Granted
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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the present invention relates to a sealing device according to the preamble of claim 1.
- a turbine stage in which the blade roots of the individual blades are equipped with a double-walled bulkhead. Furthermore, the individual blades are held in the axial direction by further sealing plates, which at the same time seal the blade root section, wherein the further sealing plates are used both at a designated edge of the inner rotor and at one edge of the blade root. Since the sealing plates are also provided as attachment of the blades, they experience high mechanical stresses in both the axial and in the radial direction, which can lead to failure of the sealing properties between the plates as the life progresses. Furthermore, at the ends of the bulkhead walls on the blade root high voltage peaks caused by the torsion of the blade, centrifugal forces and more
- GB 1 295 003 discloses a rotor for a turbomachine having a plurality of blades with blade roots which are positioned at a regular distance by engagement of lateral bimetallic plates at the periphery of a rotor.
- the rotor and the blades to be mounted on a U-shaped edge, in which the bimetallic plates are latched.
- a sealing arrangement for the rotor of a turbomachine for sealing between a blade root and a laterally arranged heat shield is known.
- T-shaped sealing elements in designated slots of the blade root and the heat shield added.
- the seal assembly uses sealing elements, which do not serve as fasteners in contrast to the aforementioned prior art.
- the mechanical loads on the sealing elements are reduced, and the sealing properties are no longer so drastically dependent on the service life of the components.
- this method is very time consuming and costly both in component manufacture and connected during assembly of the blades on the inner rotor. Furthermore, massive and thus heavy components are necessary because of the slots.
- the invention is therefore based on the object to avoid the disadvantages of the known solutions of the prior art and to provide an improved solution for sealing the flow cross-section of a rotor. Furthermore, a solution is to be provided which allows a simple and cost-effective production of the sealing devices for sealing the flow cross section of a rotor, whereby the assembly time of the individual blades is reduced on the rotor and the performance of the turbomachine is increased. At the same time, the mechanical stresses to which the ends of the bulkhead walls are exposed at the blade root should also be reduced and a secure, permanent sealing of the flow cross-section and of a rotor of a turbomachine should be made possible.
- the erfmdungshiele sealing device for sealing the rotor of a
- Turbomachine is located on the blade shank of the blades of a Rotor stage of an axial flow machine, wherein a plurality of blades are arranged in the circumferential direction side by side on the rotor.
- the sealing device has on the blade shank in the axial direction to the front and rear protruding bottom plates and in the radial direction along the blade shank extending bulkheads, which form a double-walled seal in the axial direction.
- the transition cross section from the bottom plates to the bulkheads is preferably rounded, or parabolic.
- at least one of the two bulkhead walls is offset inwards with respect to the blade root edge in the direction of the radial longitudinal axis of the blade shaft.
- the Schaufelfußrandes in the direction of the radial longitudinal axis of the blade shank is also achieved that the Schaufelfußmati is reduced in the axial direction.
- This reduction in blade root length allows for less costly component fabrication because less material is required for the component, as well as increased turbomachine performance, as it reduces the overall weight of the machine.
- a reduced risk of breakage is achieved in the case of existing plate shear due to the influence of high temperatures and centrifugal forces in the operation of the turbomachine.
- the homogeneous distribution of the mechanical stresses at the base of the blade also causes a lower concentrated concentrated material stress of the component, which is gentle on the components and results in a prolonged life.
- the sealing device also consists of a single solid component.
- two bulkhead walls which are formed in the radial direction and extend from the protruding bottom plates in the direction of the rotor axis, have a total parabolic shape.
- a sealing device which consists of two interconnected T-pieces and is connected to a blade shank of a blade, a force acts on the outwardly facing plates in a mechanical stress peak in the region of the two T-joints at the base of the blade out.
- the forces that are exerted, inter alia, on the axially protruding bottom plates of the blades result by their overall shape and by the position of the sealing device in a homogeneous distribution of mechanical stresses in the region of the blade airfoil.
- the wall thickness of the bottom plates is greater than the wall thickness of the radial bulkhead walls. This will, for example, amplify the rounded or parabolic
- Transition cross-section of the junction with the blade root table and with the radial bulkheads achieved while creating the possibility of adaptation to predetermined wider expansion slots.
- At least one of the axially protruding bottom plates and the blade root table has different inclinations.
- the sealing device according to the invention is thus applicable in a variety of different types of engines. Different inclinations are further provided as adjustment parameters for predetermined expansion slots.
- the paddle table opens in at least one of the protruding bottom plates L-shaped. This achieves a particularly efficient distribution of the forces exerted on the axially protruding bottom plates and a further homogenization of the mechanical stresses in the region of the blade airfoil, in particular if the inclination of the blade shaft and the axially protruding bottom plates are different.
- the paddle table opens into the two protruding bottom plates in a U-shape. This achieves a particularly efficient distribution of the forces exerted on the axially protruding bottom plates and a further homogenization of the mechanical stresses in the region of the blade airfoil, in particular if the inclination of the two axially protruding bottom plates is symmetrical.
- the Schaufelfußtisch is formed straight, inclined or curved.
- a straight configuration of the blade root table is particularly advantageous if the bottom plates protruding in the axial direction are likewise formed straight and in the same plane, and in particular if the turbomachine has a constant flow cross section.
- An inclined configuration of the blade root table is particularly advantageous if the bottom plates projecting in the axial direction have different inclinations and / or if the flow cross section of the turbomachine changes.
- a domed configuration of the blade root table is particularly advantageous for optimally reinforcing the joints in particular configurations of the floor panels and / or the bulkhead walls.
- the blade and the sealing device are integrally formed.
- the blade and the sealing device form two separate components, which are arranged against one another.
- the separately produced components can be connected to one another by welding, for example, and the sealing device can be coated with a friction-reducing coating.
- the device according to the invention for sealing the flow cross-section of a rotor is used both in turbines and in compressors of gas turbine plants and generally in turbomachines.
- Fig. 1 is a schematic longitudinal section through a portion of a rotor stage
- Fig. 5 including a sealing device 2 according to the present invention
- FIG. 2 shows a schematic longitudinal section through the sealing device 2 according to the first advantageous embodiment of the invention.
- 3 shows a schematic longitudinal section through the sealing device 2 according to the second advantageous embodiment of the invention;
- Fig. 4 is a schematic longitudinal section through the sealing device 2 according to the third advantageous embodiment of the invention.
- Fig. 1 shows a part of a rotor on which a blade is arranged, which contains a preferred embodiment of the invention. For the sake of clarity, only the pictured section will be discussed below, but repeated over the entire circumference of the rotor.
- the laterally indicated adjacent to the rotor shaft components 11 have rounded corners and define respective expansion slots 3 for receiving the axially protruding bottom plate 6 of the sealing element 2.
- Each sealing element 2 has a Schaufelfußtisch 8 with two projecting in the axial direction bottom plates 6 and two to Center of the rotor 5 directed and connected to the axially projecting bottom plate 6 connected parabolic bulkhead 7, 7 '.
- the sealing elements 2 can be regarded as segments of a ring in which the blade root tables 8 are arranged radially, and in which the bulkheads 7, T define a double-walled sealing ring disc.
- the sealing ring disc segments are strongly compressed so that no leakage flow can form between the adjacent ends of the individual segments. At the same time, enough space for the expansion caused by the operating temperature in the circumferential direction of the sealing members 2 is left.
- FIG. 1 is also indicated how each axially projecting bottom plate is housed in a radially and extending in the circumferential direction expansion slot 3, which is formed by arranged on the rotor shaft 5 laterally disposed components 11. This already reduces the leakage flow due to the reduced open area.
- the device comprises a sealing device 1, which contains two parabolic trained bulkheads 7, T, which are offset with respect to the Schaufelfußrandes 14, 14 'in the axial direction to each other.
- a sealing device 1 which contains two parabolic trained bulkheads 7, T, which are offset with respect to the Schaufelfußrandes 14, 14 'in the axial direction to each other.
- a stable seal is provided, which is integrated into the blade and which is furthermore not used as a fastening of the blade to the rotor, so that the sealing device 2, apart from the expansion caused by the operating temperature and centrifugal forces, is not exposed to additional mechanical stresses.
- Fig. 2 shows a longitudinal section through the sealing device 2, according to a first preferred embodiment of the invention.
- the axially protruding bottom plates 6 and the Schaufelfußtisch 8 have the same inclination and are in the same plane.
- the bulkheads 7, 7 ' extending downwardly and radially form with the protruding bottom plates 6 and with the blade root table 8 rounded connections and run in the direction of the rotor axis.
- the wall thickness of the blade root table 8, the bottom plates 6 and the bulkheads 7, T is equal.
- the sealing device 1 has two differently designed bulkhead walls 1, T.
- the right in the plane of the bulkhead T is L-shaped and runs parallel to the longitudinal axis 13 of the blade shank 4, while the left in the drawing plane bulkhead 7 in the direction of the longitudinal axis 13 of the blade shank 4 straight and offset with respect to the Schaufelfußrandes 14 inside ,
- the offset 12 of the left in the plane of the bulkhead 7 with respect to the Schaufelf trainsrandes 14 in the direction of the radial longitudinal axis 13 of the blade shank 4 are the
- Fig. 3 shows a longitudinal section through the sealing device 2, according to a second preferred embodiment of the invention.
- the bottom plates 6 protruding in the axial direction and the blade foot table 8 have different Inclinations and lie on different levels.
- the parabolic bulkheads 7, 7 'extending after the rotor center and in the radial direction form parabolic connections with the protruding bottom plates 6 and with the blade root table 8 and extend parabolically in the direction of the rotor axis and subsequently parallel to one another.
- the wall thickness of the blade root table 8 and the bottom plates 6 is greater than the wall thickness of the bulkheads 7, 7 '.
- the right in the plane of the bulkhead wall 7 ' is also in the direction of the longitudinal axis 13 of the blade shank 4 first parabolic and then straight and offset with respect to the Schaufelfußrandes 14' to the inside.
- the offset 12 of the right in the plane of the bulkhead wall 7 'with respect to the Schaufelfußrandes 14' in the direction of the radial longitudinal axis 13 of the blade shank 4 are significantly reduced, as a result, the power flow of the introduced forces is optimized.
- FIG. 4 shows a longitudinal section through the sealing device 2, according to a third preferred embodiment of the invention.
- the bottom plates 6 projecting in the axial direction as well as the blade root table 8 have the same inclination, they lie on different planes
- the bulkheads 7, T extending towards the rotor center and in the radial direction and forming a parabolic taper form the protruding bottom plates 6 and rounded off connections to the blade root table 8 and run parabolically in the direction of the rotor axis
- the wall thickness of the bulkheads 7, 7 ' is greater than the wall thickness of the blade root table 8 and the bottom plates 6. Die in the
- Drawing plane right bulkhead 7 ' is also in the direction of the longitudinal axis 13 of the blade shank 4, d, h. in the radial direction with respect to the axial flow machine, first parabolic and then rectilinear. In this case, approximately the last third is formed as a straight line in the present embodiment, while the first two thirds of the blade shank 4 form approximately a parabola. With respect to the Schaufelfußrandes 14 'is in the plane of the drawing right bulkhead 7 'offset inside.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102009007664A DE102009007664A1 (de) | 2009-02-05 | 2009-02-05 | Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine |
PCT/DE2010/000105 WO2010088881A1 (de) | 2009-02-05 | 2010-02-02 | Abdichtvorrichtung an dem schaufelschaft einer rotorstufe einer axialen strömungsmaschine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2394028A1 true EP2394028A1 (de) | 2011-12-14 |
EP2394028B1 EP2394028B1 (de) | 2016-06-01 |
Family
ID=42126369
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10710168.5A Not-in-force EP2394028B1 (de) | 2009-02-05 | 2010-02-02 | Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine und ihre Verwendung |
Country Status (5)
Country | Link |
---|---|
US (1) | US8870542B2 (de) |
EP (1) | EP2394028B1 (de) |
DE (1) | DE102009007664A1 (de) |
ES (1) | ES2576125T3 (de) |
WO (1) | WO2010088881A1 (de) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2597266B1 (de) | 2011-11-22 | 2014-08-27 | MTU Aero Engines GmbH | Laufschaufel und Strömungsmaschine |
FR2997723B1 (fr) * | 2012-11-06 | 2018-09-21 | Safran Aircraft Engines | Aube a pied munie de portions en depression |
US9353629B2 (en) * | 2012-11-30 | 2016-05-31 | Solar Turbines Incorporated | Turbine blade apparatus |
FR3004484B1 (fr) | 2013-04-11 | 2017-09-08 | Snecma | Aube de turbomachine cooperant avec un disque de retention d'aubes |
EP2818639B1 (de) | 2013-06-27 | 2019-03-13 | MTU Aero Engines GmbH | Turbomaschinenlaufschaufel und zugehörige Turbomaschine |
Family Cites Families (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL98166C (de) * | 1953-12-02 | |||
GB1148339A (en) * | 1966-10-20 | 1969-04-10 | Rolls Royce | Compressors or turbines for gas turbine engines |
GB1295003A (de) | 1971-06-15 | 1972-11-01 | ||
FR2485632B1 (fr) * | 1980-06-30 | 1985-07-05 | Snecma | Perfectionnement aux systemes de ventilation des aubes et disques de turbines |
US4536129A (en) * | 1984-06-15 | 1985-08-20 | United Technologies Corporation | Turbine blade with disk rim shield |
FR2586061B1 (fr) * | 1985-08-08 | 1989-06-09 | Snecma | Disque porte labyrinthe multifonction pour rotor de turbomachine |
DE3743253A1 (de) * | 1987-12-19 | 1989-06-29 | Mtu Muenchen Gmbh | Axial durchstroemtes laufschaufelgitter fuer verdichter oder turbinen |
US5131814A (en) | 1990-04-03 | 1992-07-21 | General Electric Company | Turbine blade inner end attachment structure |
US5302085A (en) * | 1992-02-03 | 1994-04-12 | General Electric Company | Turbine blade damper |
US5443365A (en) * | 1993-12-02 | 1995-08-22 | General Electric Company | Fan blade for blade-out protection |
JPH08121106A (ja) * | 1994-10-26 | 1996-05-14 | Mitsubishi Heavy Ind Ltd | タービン動翼 |
GB2302711A (en) | 1995-06-26 | 1997-01-29 | Bmw Rolls Royce Gmbh | A turbine disc with blade seal plates |
JP2002544430A (ja) * | 1999-05-14 | 2002-12-24 | シーメンス アクチエンゲゼルシヤフト | ロータに対する漏れ止め装置付き流体機械特にガスタービン |
EP1371814A1 (de) | 2002-06-11 | 2003-12-17 | ALSTOM (Switzerland) Ltd | Dichtungsanordnung für den Rotor einer Gasturbine |
US7244104B2 (en) * | 2005-05-31 | 2007-07-17 | Pratt & Whitney Canada Corp. | Deflectors for controlling entry of fluid leakage into the working fluid flowpath of a gas turbine engine |
US7334983B2 (en) * | 2005-10-27 | 2008-02-26 | United Technologies Corporation | Integrated bladed fluid seal |
DE102005059084A1 (de) * | 2005-12-10 | 2007-06-14 | Mtu Aero Engines Gmbh | Turbomaschine, insbesondere Gasturbine |
US7575416B2 (en) * | 2006-05-18 | 2009-08-18 | United Technologies Corporation | Rotor assembly for a rotary machine |
EP1898049B1 (de) * | 2006-09-11 | 2012-05-23 | Siemens Aktiengesellschaft | Turbinenschaufel |
US20080101937A1 (en) * | 2006-10-26 | 2008-05-01 | General Electric | Blade/disk dovetail backcut for blade/disk stress reduction (9FA, stage 1) |
FR2918103B1 (fr) * | 2007-06-27 | 2013-09-27 | Snecma | Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine. |
-
2009
- 2009-02-05 DE DE102009007664A patent/DE102009007664A1/de active Pending
-
2010
- 2010-02-02 US US13/148,026 patent/US8870542B2/en active Active
- 2010-02-02 WO PCT/DE2010/000105 patent/WO2010088881A1/de active Application Filing
- 2010-02-02 ES ES10710168.5T patent/ES2576125T3/es active Active
- 2010-02-02 EP EP10710168.5A patent/EP2394028B1/de not_active Not-in-force
Non-Patent Citations (1)
Title |
---|
See references of WO2010088881A1 * |
Also Published As
Publication number | Publication date |
---|---|
ES2576125T3 (es) | 2016-07-05 |
US20110293408A1 (en) | 2011-12-01 |
WO2010088881A1 (de) | 2010-08-12 |
US8870542B2 (en) | 2014-10-28 |
EP2394028B1 (de) | 2016-06-01 |
DE102009007664A1 (de) | 2010-08-12 |
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