IL47321A - Turbine engine - Google Patents
Turbine engineInfo
- Publication number
- IL47321A IL47321A IL47321A IL4732175A IL47321A IL 47321 A IL47321 A IL 47321A IL 47321 A IL47321 A IL 47321A IL 4732175 A IL4732175 A IL 4732175A IL 47321 A IL47321 A IL 47321A
- Authority
- IL
- Israel
- Prior art keywords
- disk
- face
- root
- blades
- turbine
- Prior art date
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
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
-
- 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
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/50—Vibration damping features
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
TURBINE ENGINE This invention relates to gas turbine engines and more particularly to the axial sealing of turbine wheels.
Gas turbine wheel assemblies commonly comprise a plurality of turbine blades each of which is joined to a disk through the engagement of the fi tree blade root in a corresponding disk slot and extends radially outward from the periphery of the disk.
Each blade has a platform section which is spaced radially from the blade root by a neck extension. The cylinder formed by the platforms when all blades are in place defines the inner diameter wall of the working medium flow path.
The platforms of two adjacent blades, in conjunction with the di¾k rim and the neck extensions of the two adjacent blades forms an axially oriented cavity which contains a vibration damper.
During rotation of the turbine wheel, centrifugal force urges the damper to bear upon the undersurfaces of the two adjacent blade platforms. Vibration occurring in any turbine blade is coupled into the adjacent blades through the vibration dampers. Each damper forms mechanical bridge between the blade platforms of adjacent blades thereby tending to equalize the frequency of blade vibration throughout the wheel assembly. In addition vibratory energy is diminished by the friction between dampers and the blade platforms.
In modern gas turbine engines it is essential that the damper cavity be sealed to prevent leakage of the working medium from the main flow path and to prevent the flow of working medium, which is comprised of hot gases, against the rim of the disk.
A typical wheel construction including vibration damper cavities is shown in U. S. Patent No. 3,666,376 to Damlis. Each damper cavity contains a vibration damper; a fully-annular sideplate seals each side of the turbine disk.
An increase in either the temperature in the turbine or the diameter of the wheel assembly causes a corresponding increase in thermal distortion of the sideplates. This distortion results in substantial leakage between the side-plate and the disk. Increasing the mass of the sideplate is one-way to reduce distortion, however, the size and weight of the disk required to restrain the sideplate centrifugal loads correspondingly increase.
Alternate apparatus for sealing the cavity between the blade platforms and the disk rim are shown in U. S. Patent No. 3,610,778 to Suter and U. S. Patent No. 3,119,595 to Wilson et al. In Wilson the open end of a baffle member formed to a cup shaped configuration surrounds the disk rim between two adjacent blade roots. The base of the cup contacts the undersides of two adjacent blade platforms and absorbs vibrational energy imparted to it by the blade platforms. The sides of the cup contact the neck extensions of the two adjacent blades thereby substantially filling the - - axial cavity.
Suter also discloses a vibration damper which simultaneously fills the axial cavity while damping blade vibration. Although the dampers' described in Wilson and Suter substantially fill the axial cavity, apparatus for sealing the axial interface between the damper and the blade root is not provided. Similarly, in the constructions of Suter and Wilson the interface between the turbine blade roots and the disk remains unsealed thereby permitting the escape of working medium from the main flow path.
The addition of conventional annular sideplates to the wheel assemblies of Suter and Wilson for the purpose of covering the described interfaces results in a wheel assembly that is subject to the same limitations described with respect to the-Damlis construction. As the size of gas turbine engines continues to increase, the larger wheel diameters are making it increasingly impractical to hold wide side-plates in surface contact with the disk and methods are necessary to appropriately secure the seal members to the turbine wheel at the blade roots.
A primary object of the present invention is to prevent leakage of working medium in the axial direction across a turbine wheel assembly and to prevent the flow of hot gases against the disk rim. An additional object of the present invention is to provide damping of tangential vibrations in the blades of a turbine.
. . According to the present invention, there is provided, in a gas turbine having an axis of rotation, a wheel assembly comprising : a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation; a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension; a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades; a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the seal plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly; a first side late which is in surface contact with the first face of the disk and covers the root portions of a plurality of turbine blades; and a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
According to another aspect of the present invention, there is provided, in a gas turbine engine having an axis of rotation, a wheel assembly of the type wherein a plurality P.A. 47321/2 of blades is attached to a turbine disk and extend radially from the disk, the disk having a face which is substantially perpendicular to the axis of rotation and a circumferentially extending rim with root connecting means spaced about the rim, and each blade having a root which engages the root connecting means of the disk and a blade platform joined to the root by a neck extension, and wherein a plurality of seal plates is held in contact with the disk face and the neck extensions of two adjacent blades to prevent the leakage of working medium in the axial direction across the wheel assembly, the improvement which comprises: means responsive to centrifugal force to urge each seal plate against the face of the disk and to damp vibration in the blades, said means responsive to centrifugal force comprising: a support which is integral with the seal plate, extends axially between the neck extensions of two adjacent blades, and has a surface which extends from the seal plate and is inclined in a direction away from the axis of rotation; nd a vibration damper which is axially restrained by the disk and has a sloped surface substantially parallel to, aaad in contact with, the inclined surface of the seal plate.
A principal advantage of the present invention is a reduction in a quantity of working medium leaking across the wheel assembly. Also the wheel construction in accordance with the present invention results in a significantly reduced mass at the outer diameter of the sideplates.
Relative movement between the damper and the seal plate along the slope surface of the damper is encouraged by vibrations of the damper which interrupt the friction forces P.A. 47321/2 at the interface between the damper and the seal plate.
The foregoing and other objects, features and advantages of the present invention will become more apparent in the light of the following detailed description of the preferred embodiments thereof as illustrated in the accompanying drawings.
Fig. 1 is a partially broken away rear elevation view of a portion of a turbine wheel assembly showing apparatus for axially sealing the vibration damper cavity and the interface between the blade root and the disk; Fig. 2 is a section view taken along the line 2-2 as shown in Fig. 1: Fig. 3 is a perspective view of the seal plate which is shown in cross section in Fig. 2; Fig. 4 is a perspective view of the vibration damper which is shown in cross section in Fig. 2; and Fig. 5 is a section view corresponding to Fig. 2 showing alternate apparatus for axially sealing the vibration damper cavity. Ί Fig. 1 shows a turbine wheel assembly 10 including a disk 12 having a rim 14 and a plurality of fir tree type connecting slots 16 each of which engages a correspondingly shaped root 18 of a blade 20. Each blade has a platform section 22 spaced apart from the root by a neck extention 24. The neck extensions of two adjacent blades form the sidewalls 26 of an axially oriented damper cavity 28. The rim forms the inner wall of the cavity and the undersides 30 of the platforms of the two adjacent blades form the outer wall of the cavity. As shown in Fig. 2, the end walls of the damper cavity are formed by a seal plate 32 on the low pressure side of the wheel assembly and by an end plate extension 34 of a vibration damper 36 on the high pressure side of the wheel assembly. As shown in Fig. 3 the seal plate 32 includes a support section 38 having an inclined surface 40 extending from the seal plate in a direction away from the axis of rotation of the wheel assembly. The vibration damper has a sloped surface 42 which is essentially parallel to the inclined surface of the seal plate and a pair of platform sealing surfaces 44 as shown in Fig. 4. £ low pressure sideplate 46 having a long offset 48 which extends around its circumference is bolted to a low pressure face 50 of the disk and traps the seal plate between the low pressure sideplate and the disk. Similarly, a high pressure sideplate 52 having a short offset 54 which extends around its circumference is bolted to a high pressure face 56 of Jthe disk and traps the end plate of the vibration damper between the high pressure sideplate and the disk as is shown in Fig. 2.
To assemble the turbine wheel, the root of each blade '. is inserted into a fir tree shaped slot in the disk and a seal plate is positioned against the disk between two adjacent blades with the support section 38 extending into the damper cavity 28. With all the blades and seal plates in position the low pressure sideplate 46 is affixed to the disk trapping the seal plates on the wheel assembly between the long offset 48 on the sideplate and the low pressure face of the disk. The seal plates are adjusted to a lowered position as represented by the dotted line in Fig. 2, and a vibration dam er 36 is inserted into each dam er cavit .
A high pressure sideplate 52 is affixed to the disk trapping the end plate extensions 34 of the vibration dampers between the short offset 54 on the sideplate and the high pressure face of the disk. Both the seal plate and the vibration damper are free to move axially and radially within limits permitted by the turbine blades, the disk and the sideplates as shown in Fig. 2.
During operation of the gas turbine engine, centrifugal loads force the individual components radially away from the axis of rotation. Each turbine blade is restrained by the . disk slot and each vibration damper is restrained b the blade platforms. The sloped surface 42 of each vibration damper engages and restrains the seal plate as the plate tends to move radially.
Each turbine blade has sufficient clearance between the blade root and the disk slot to allow limited tangential or circumferential movement of the blade when vibrationally excited. During a period of vibrational excitation, the movement of the blade is resisted by the dampers, which under the influence of centrifugal force, bear against the underside of the platform of the excited blade as well as the undersides of the next adjacent blade platforms.
Fractional forces at the points of contact between the dampers and the blade platforms are energ dissipative and reduce the detrimental effects of blade vibration. The seal plate bears upon the vibration damper and effectively increases the mass of the damper with a corresponding increase in the damping effects. The sealing surfaces 44 on the vibration damper bear against the undersides of the two adjacent turbine blades to effect a radial seal between the platforms of two adjacent blades and to prevent the circulation working medi-um, which is comprised of hot gases from the main flow path, against the rim of the disk.
The centrifugal force due to each seal plate during rotation is transferred to the corresponding vibration damper across the slope surface 42. The force has a component which tends to draw the seal plate and the vibration damper together until the seal plate and the end plate extension 34 on the vibration damper abut the low and high pressure faces respectively of the disk. When the sloped surface of the vibration damper and inclined surface of the seal p'late are in contact friction forces resist their relative movement. However, as the damper vibrates the contact is interrupted thereby reducing the frictional resistance and permitting the seal plate and damper to reposition by sliding.
The high and low pressure sideplates, acting in a conventional manner, seal the interfaces between the turbine blade roots and the disk.
The alternative embodiment shown in Fig. 5 incorporates seal plates on both the high and low pressure sides of the wheel assembly. An independent vibration damper 58 having a pair of sloped surfaces 60 is located within the damper . cavity. A pair of the seal plates 32 engage the damper, the inclined surface 38 of each seal plate engaging the correspondingly sloped surface on the damper.
The seal plates on the high and low pressure sides of the disk are drawn toward the vibration damper 58 by the axial components of centrifugally generated forces. The embodiment of Fig. 5 is particularly attractive where the movement of the damper within the cavity due to vibration is excessive and where such movement would detrimentally increase the amount of working medium leaking between the end plate extension of the vibration damper and the high pressure face of the disk.
Although the contact between the seal plate and the vibration damper has been described with respect to engaged surfaces a construction where the contact is at a point "meeting an inclined surface is equally effective. For example, an embodiment of the invention ma include a protrusion extending from the inclined surface 40 of the seal plate shown in Fig. 3, the protrusion bearing upon the sloped surface of the vibration damper.
The sideplates of the present invention have a greatly reduced radial width. Conventional sideplates require sufficient mass at their outer diameter to resist thermal distortion as the sideplates are subjected to unequally distributed temperatures. The seal plates which cover only a local area are not subjected to the severe' temperature gradients and may, therefore, be fabricated from material « having a lesser thickness while experiencing less thermal distortion.
The axial forces generated by the seal plate during rotation are sufficient to hold the seal plate and the end plate extension of the vibration damper in surface contact with the turbine disk and the turbine blade roots, precluding a requirement for additional attaching members .
Although the invention has been described with respect s to an axially oriented damper cavity the concepts disclosed equally apply where the cavity is oriented diagonal to the axis of the turbine wheel.
Although the invention has been shown and described with respect to the preferred embodiments thereof, it should be understood by those skilled in the art that the foregoing and other changes and omissions in the form and detail thereof can be made therein without departing from the spirit and the scope of the invention.
Having thus described a typical embodimen of our invention, that which we claim as new and desire to secure by Letters Patent of the United States is:
Claims (7)
1. In a gas turbine having an axis of rotation, a wheel assembly comprising: a turbine disk having a circumferentially extending rim with root connecting means spaced along the rim and first and second faces which are substantially perpendicular to the axis of rotation; a plurality of turbine blades extending radially from the disk, each blade having a root which engages the root connecting means and a platform spaced apart radially from the root by a neck extension; a plurality of seal plates, each of which abuts the first face of the disk at the rim and the neck extensions of two adjacent turbine blades and has a support section extending between the neck extensions of the adjacent blades; a plurality of vibration dampers each of which is located between the neck extensions of two adjacent blades in a position radially outward from the support of the seal plate, and has a sloped surface facing, and in contact with, the support section of the seal plate which is urged against the first face of the disk by axial components of centrifugal loads during rotation of the wheel assembly; a fitrst sideplate which is in sufface contact with the first face of the disk and covers the root portions of a plurality of turbine blades ; and a second sideplate which is in surface contact with the second face of the disk and covers the root portions of a plurality of turbine blades.
2. The invention according to Claim 1 wherein the support seccxon has an inclined surface substantially parallel to, and in contact with, the sloped surface of the vibration P.A. 47321/2
3. The invention according to Claim 1 wherein the vibration damper further has an end plate extension which abuts the second face of the disk at the rim and the neck extensions of the two adjacent blades, and a pair of sealing surfaces, each of which is in contact with the undersurface of the platform of one of the adjacent blades, whereby the end plate extension of the vibration damper is urged against the second face of the disk by axial components of centrifugal loads during rotation of the wheel assembly and whereby the sealing surfaces of the vibration damper are held in contact with the platforms by radial components of centrifugal loads.
4. The invention according to Claim 1 wherein the first sideplate has a circumferential offset at its periphery which engages and retains the seal plates between the offset and the first face of the disk.
5. The invention according to Claim 1 wherein the second sideplate has a circumferential offset at its periphery which engages and retains the vibration dampers between the offset and the second face of the disk.
6. In a gas turbine engine having an axis of rotation, a wheel assembly of the type wherein a plurality of blades is attached to a turbine disk and extend radially from the disk, the disk having a face which is substantially perpendicular to the axis of rotation and a circumferentially extending tim with root connecting means spaced about the rim, and each blade having a root whi¾h engages the root connecting means of the disk and a blade platform joined to the root by a neck extension, and wherein a plurality of seal plates is held in contact with the disk face and the neck extensions of two adjacent blades to prevent the leakage of working P.A. 47321/2 the Improvement which comprises : means responsive to centrifugal force to urge each seal plate against the face of the disk and to damp vibration in the blades, said means responsive to centrifugal force comprising : a support which is integral with the seal plate, extends axially between the neck extensions of two adjacent blades, and has a surface which extends from the seal plate and is inclined in a direction away from the axis of rotation; and a vibration damper which is axially restrained by the disk and has a sloped surface substantially parallel to, and in contact with, the inclined surface of the seal plate.
7. Gas turbine substantially as hereinbefore described with reference to and as illustrated in the accompanying drawings.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US474756A US3887298A (en) | 1974-05-30 | 1974-05-30 | Apparatus for sealing turbine blade damper cavities |
Publications (2)
Publication Number | Publication Date |
---|---|
IL47321A0 IL47321A0 (en) | 1975-07-28 |
IL47321A true IL47321A (en) | 1977-07-31 |
Family
ID=23884811
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
IL47321A IL47321A (en) | 1974-05-30 | 1975-05-20 | Turbine engine |
Country Status (8)
Country | Link |
---|---|
US (1) | US3887298A (en) |
JP (1) | JPS5113012A (en) |
BR (1) | BR7503391A (en) |
CA (1) | CA1013676A (en) |
FR (1) | FR2273163A1 (en) |
GB (1) | GB1506047A (en) |
IL (1) | IL47321A (en) |
SE (1) | SE7505935L (en) |
Families Citing this family (51)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3957393A (en) * | 1974-10-29 | 1976-05-18 | United Technologies Corporation | Turbine disk and sideplate construction |
GB1512882A (en) * | 1976-02-11 | 1978-06-01 | Rolls Royce | Bladed rotor assembly for a gas turbine engine |
US4088421A (en) * | 1976-09-30 | 1978-05-09 | General Electric Company | Coverplate damping arrangement |
US4101245A (en) * | 1976-12-27 | 1978-07-18 | United Technologies Corporation | Interblade damper and seal for turbomachinery rotor |
GB2043796B (en) * | 1979-03-10 | 1983-04-20 | Rolls Royce | Bladed rotor for gas turbine engine |
US4473337A (en) * | 1982-03-12 | 1984-09-25 | United Technologies Corporation | Blade damper seal |
FR2523208A1 (en) * | 1982-03-12 | 1983-09-16 | Snecma | DEVICE FOR DAMPING MOBILE TURBINE BLADE VIBRATIONS |
US4480957A (en) * | 1983-04-14 | 1984-11-06 | General Electric Company | Dynamic response modification and stress reduction in dovetail and blade assembly |
US4568247A (en) * | 1984-03-29 | 1986-02-04 | United Technologies Corporation | Balanced blade vibration damper |
US4659285A (en) * | 1984-07-23 | 1987-04-21 | United Technologies Corporation | Turbine cover-seal assembly |
FR2585069B1 (en) * | 1985-07-16 | 1989-06-09 | Snecma | DEVICE FOR LIMITING THE ANGULAR DEFLECTION OF BLADES MOUNTED ON A TURBOMACHINE ROTOR DISC |
FR2586061B1 (en) * | 1985-08-08 | 1989-06-09 | Snecma | MULTIFUNCTIONAL LABYRINTH DISC FOR TURBOMACHINE ROTOR |
US4743164A (en) * | 1986-12-29 | 1988-05-10 | United Technologies Corporation | Interblade seal for turbomachine rotor |
US4872810A (en) * | 1988-12-14 | 1989-10-10 | United Technologies Corporation | Turbine rotor retention system |
GB2228541B (en) * | 1989-02-23 | 1993-04-14 | Rolls Royce Plc | Device for damping vibrations in turbomachinery blades |
US5201849A (en) * | 1990-12-10 | 1993-04-13 | General Electric Company | Turbine rotor seal body |
US5226784A (en) * | 1991-02-11 | 1993-07-13 | General Electric Company | Blade damper |
US5339619A (en) * | 1992-08-31 | 1994-08-23 | United Technologies Corporation | Active cooling of turbine rotor assembly |
US5281097A (en) * | 1992-11-20 | 1994-01-25 | General Electric Company | Thermal control damper for turbine rotors |
US5228835A (en) * | 1992-11-24 | 1993-07-20 | United Technologies Corporation | Gas turbine blade seal |
US5313786A (en) * | 1992-11-24 | 1994-05-24 | United Technologies Corporation | Gas turbine blade damper |
US5284421A (en) * | 1992-11-24 | 1994-02-08 | United Technologies Corporation | Rotor blade with platform support and damper positioning means |
US5388962A (en) * | 1993-10-15 | 1995-02-14 | General Electric Company | Turbine rotor disk post cooling system |
FR2726323B1 (en) * | 1994-10-26 | 1996-12-13 | Snecma | ASSEMBLY OF A ROTARY DISC AND BLADES, ESPECIALLY USED IN A TURBOMACHINE |
US5573375A (en) * | 1994-12-14 | 1996-11-12 | United Technologies Corporation | Turbine engine rotor blade platform sealing and vibration damping device |
US5513955A (en) * | 1994-12-14 | 1996-05-07 | United Technologies Corporation | Turbine engine rotor blade platform seal |
US5827047A (en) * | 1996-06-27 | 1998-10-27 | United Technologies Corporation | Turbine blade damper and seal |
US5785499A (en) * | 1996-12-24 | 1998-07-28 | United Technologies Corporation | Turbine blade damper and seal |
US5924699A (en) * | 1996-12-24 | 1999-07-20 | United Technologies Corporation | Turbine blade platform seal |
US6139277A (en) * | 1998-12-22 | 2000-10-31 | Air Concepts, Inc. | Motorized fan |
US6273683B1 (en) | 1999-02-05 | 2001-08-14 | Siemens Westinghouse Power Corporation | Turbine blade platform seal |
US6932575B2 (en) * | 2003-10-08 | 2005-08-23 | United Technologies Corporation | Blade damper |
US7484936B2 (en) * | 2005-09-26 | 2009-02-03 | Pratt & Whitney Canada Corp. | Blades for a gas turbine engine with integrated sealing plate and method |
US7762780B2 (en) * | 2007-01-25 | 2010-07-27 | Siemens Energy, Inc. | Blade assembly in a combustion turbo-machine providing reduced concentration of mechanical stress and a seal between adjacent assemblies |
US8128371B2 (en) | 2007-02-15 | 2012-03-06 | General Electric Company | Method and apparatus to facilitate increasing turbine rotor efficiency |
FR2923557B1 (en) * | 2007-11-12 | 2010-01-22 | Snecma | BLOWER DRAWER ASSEMBLY AND ITS SHOCK ABSORBER, BLOWER DAMPER AND METHOD FOR CALIBRATING THE SHOCK ABSORBER |
EP2379845A4 (en) * | 2008-12-18 | 2013-08-07 | Gkn Aerospace Sweden Ab | Gas turbine composite workpiece to be used in gas turbine engine |
DE102009011879A1 (en) * | 2009-03-05 | 2010-09-16 | Mtu Aero Engines Gmbh | Integrally bladed rotor and method of making an integrally bladed rotor |
GB2491121B (en) * | 2011-05-23 | 2014-10-01 | Rolls Royce Plc | Balancing of rotatable components |
US10287897B2 (en) * | 2011-09-08 | 2019-05-14 | General Electric Company | Turbine rotor blade assembly and method of assembling same |
US9366142B2 (en) * | 2011-10-28 | 2016-06-14 | General Electric Company | Thermal plug for turbine bucket shank cavity and related method |
US9279332B2 (en) * | 2012-05-31 | 2016-03-08 | Solar Turbines Incorporated | Turbine damper |
US9650901B2 (en) * | 2012-05-31 | 2017-05-16 | Solar Turbines Incorporated | Turbine damper |
BR112015000081A2 (en) | 2012-06-30 | 2017-06-27 | Gen Electric | turbine blade sealing structure. |
JP6240786B2 (en) | 2013-09-11 | 2017-11-29 | ゼネラル・エレクトリック・カンパニイ | Ply structure for integral platform and damper retention features of CMC turbine blades |
ES2622424T3 (en) * | 2013-09-17 | 2017-07-06 | MTU Aero Engines AG | Blade impeller of an axial circulation machine and damping element |
EP2873807A1 (en) * | 2013-11-18 | 2015-05-20 | Siemens Aktiengesellschaft | Cover plate, rotor blade, wheel disc, bolt and gas turbine |
EP3380704B1 (en) | 2016-01-12 | 2023-09-06 | Siemens Energy Global GmbH & Co. KG | Flexible damper for turbine blades |
ES2891084T3 (en) * | 2016-04-27 | 2022-01-26 | MTU Aero Engines AG | Turbomachinery Vane Assembly |
US10941671B2 (en) * | 2017-03-23 | 2021-03-09 | General Electric Company | Gas turbine engine component incorporating a seal slot |
CN111448365B (en) * | 2017-12-12 | 2023-02-28 | 赛峰直升机发动机公司 | Vibration damper for a turbine rotor blade |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB779059A (en) * | 1954-07-15 | 1957-07-17 | Rolls Royce | Improvements in or relating to axial-flow fluid machines, for example compressors orturbines of gas-turbine engines |
GB802476A (en) * | 1955-09-29 | 1958-10-08 | Rolls Royce | Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines |
US3112915A (en) * | 1961-12-22 | 1963-12-03 | Gen Electric | Rotor assembly air baffle |
US3181835A (en) * | 1964-01-07 | 1965-05-04 | Carroll C Davis | Blade vibration damping device |
CH494896A (en) * | 1968-08-09 | 1970-08-15 | Sulzer Ag | Mounting of rotor blades in the rotor of a turbomachine |
BE791375A (en) * | 1971-12-02 | 1973-03-01 | Gen Electric | DEFLECTOR AND SHOCK ABSORBER FOR TURBOMACHINE FINS |
-
1974
- 1974-05-30 US US474756A patent/US3887298A/en not_active Expired - Lifetime
-
1975
- 1975-05-08 CA CA226,568A patent/CA1013676A/en not_active Expired
- 1975-05-20 IL IL47321A patent/IL47321A/en unknown
- 1975-05-22 GB GB22405/75A patent/GB1506047A/en not_active Expired
- 1975-05-26 SE SE7505935A patent/SE7505935L/en unknown
- 1975-05-27 FR FR7516387A patent/FR2273163A1/fr not_active Withdrawn
- 1975-05-30 JP JP50065233A patent/JPS5113012A/ja active Pending
- 1975-06-28 BR BR4336/75D patent/BR7503391A/en unknown
Also Published As
Publication number | Publication date |
---|---|
SE7505935L (en) | 1975-12-01 |
JPS5113012A (en) | 1976-02-02 |
CA1013676A (en) | 1977-07-12 |
BR7503391A (en) | 1976-04-27 |
GB1506047A (en) | 1978-04-05 |
FR2273163A1 (en) | 1975-12-26 |
US3887298A (en) | 1975-06-03 |
IL47321A0 (en) | 1975-07-28 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
IL47321A (en) | Turbine engine | |
US4361213A (en) | Vibration damper ring | |
US4455122A (en) | Blade to blade vibration damper | |
US5281097A (en) | Thermal control damper for turbine rotors | |
US4344740A (en) | Rotor assembly | |
AU629270B2 (en) | Turbine rotor retention system for reducing vibration | |
KR950006401B1 (en) | Interblade seal for turbomachine rotor | |
US2912223A (en) | Turbine bucket vibration dampener and sealing assembly | |
US4480959A (en) | Device for damping vibrations of mobile turbine blades | |
US4721434A (en) | Damping means for a stator | |
US5460489A (en) | Turbine blade damper and seal | |
EP0670956B1 (en) | Gas turbine blade damper | |
JPS63230909A (en) | Rotor assembly for rotary power machine | |
JPH057541B2 (en) | ||
JPS641642B2 (en) | ||
US4378961A (en) | Case assembly for supporting stator vanes | |
US6669443B2 (en) | Rotor platform modification and methods using brush seals in diaphragm packing area of steam turbines to eliminate rotor bowing | |
US5733103A (en) | Vibration damper for a turbine engine | |
EP0806545B1 (en) | Vibration damping pins for turbomachine shrouds | |
JPH057544B2 (en) | ||
US2888239A (en) | Turbine wheel construction | |
US8926269B2 (en) | Stepped, conical honeycomb seal carrier | |
JP2013501883A (en) | Vibration damping shim for fan blades | |
JPH056018B2 (en) | ||
JPH0477121B2 (en) |