EP1752610A2 - Gasturbinenrotor, Gasturbine und Frequenzabstimmungsverfahren für ein Gasturbinenbläser - Google Patents
Gasturbinenrotor, Gasturbine und Frequenzabstimmungsverfahren für ein Gasturbinenbläser Download PDFInfo
- Publication number
- EP1752610A2 EP1752610A2 EP06254096A EP06254096A EP1752610A2 EP 1752610 A2 EP1752610 A2 EP 1752610A2 EP 06254096 A EP06254096 A EP 06254096A EP 06254096 A EP06254096 A EP 06254096A EP 1752610 A2 EP1752610 A2 EP 1752610A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- turbine engine
- blades
- rotor
- stiffness
- 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- Withdrawn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
Images
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
- F01D5/16—Form or construction for counteracting blade vibration
Definitions
- the present invention relates to a gas turbine engine fan, and more particularly to tuning the gas turbine engine fan to reduce non-integral vibrations.
- gas turbine engine design specifically rotor and fan blade design
- rotor and fan blade design One goal of gas turbine engine design, specifically rotor and fan blade design, is to minimize non-integral vibrations caused by flutter and flow shedding. Tuning of the gas turbine engine fan has been shown to reduce non-integral vibrations in the gas turbine engine.
- One known method of tuning the gas turbine engine fan involves varying the natural frequencies of individual fan blades by removing material from the blade edges. This method is commonly referred to as "clipping.” Removing material from the blade edges changes the natural frequency of the blade, and, in so doing, may reduce the non-integral vibrations in the fan. This method typically involves modifying the blade edges after the blade is manufactured.
- Another method of tuning the gas turbine engine fan involves having fan blades with different thicknesses on the same rotor. Typically, this method uses fan blades on the rotor alternating between blades of different external profiles. Thus, both “thick” and “thin” blades are used and both “thick” and “thin” blades are manufactured.
- fan blades on a rotor will have the same general profile.
- a turbine blade has a blade shell and a blade core each having a stiffness. Adjusting the stiffness of the blade shell or blade core may change the naturally frequency of the blade. In addition to the natural frequency of the blade, these adjustments may modify other tunable characteristics, e.g., weight.
- the blade core is typically embedded in the blade shell. Accordingly, the blade core size can be modified without affecting the profile of the turbine blade. In addition, the blade core can be eliminated without changing the profile of the turbine blade.
- a turbine rotor disk containing multiple fan blades may contain fan blades with different sized blade cores.
- a turbine rotor disk may also contain one or more fan blades without blade cores.
- a metal matrix composite may be used as a blade core.
- An area of MMC material within the blade can be readily introduced to current turbine blade production techniques.
- a size of the MMC material may be adjusted to tune the gas turbine engine fan.
- a stiffness of the MMC material may be adjusted to tune the gas turbine engine fan.
- the MMC material is contained within alternating blades disposed upon the turbine rotor disk.
- the present invention therefore provides a method of tuning a fan blade without altering the profile of the fan blade.
- the method of the present invention can be readily introduced to current blade manufacturing techniques.
- a rotor disk 30 rotates a plurality of blades 22 about an axis 42.
- the rotating plurality of blades 22 moves air through the gas turbine engine 38 and may introduce non-integral vibrations, such as flutter and flow shedding, to the gas turbine engine 38.
- Non-integral vibrations may be controlled by varying the stiffness of one or more of the plurality of blades 22.
- the present invention may be incorporated into another sections of the gas turbine engine 38, such as a rotor section 46 of the gas turbine engine 38.
- the gas turbine engine 38 also includes a compressor 44 and a combustion section 48
- FIG. 2 illustrates a blade 22 tuned with materials of a dissimilar stiffness.
- the blade 22 has a blade shell portion 10 defining a cavity 14 containing a blade core portion 18.
- the blade shell portion 10 has a first stiffness and the blade core portion 18 has a second stiffness. Varying the relationship between the first stiffness and the second stiffness controls the overall stiffness of the blade 22.
- the cavity 14 is described in singular terms, it should be understood that the cavity 14 may comprise a second cavity 50 within the blade shell portion 10.
- the blade core portion 18 may comprise a porous material containing the blade shell portion 10 within the pores.
- Figure 2 also illustrates attachment structure 34.
- the attachment structure 34 operates to secure the blade 22 to the rotor disk 30.
- the attachment structure 34 facilitates removal of the blade 22 from the rotor.
- the blade shell portion 10 defines an airfoil extending from the attachment structure 34.
- FIG. 3 illustrates a section view of the blade 22 through line 3 of Figure 2.
- Figure 4 illustrates a section view of the blade 22 through line 4 of Figure 2.
- the cavity 14 defined by the blade shell portion 10 is defined within the blade 22. Varying the size of the blade shell portion 10 may vary the size of the cavity 14 and, in so doing, may accommodate different sized blade core portions 18. Varying the size of the blade shell portion 10 and the blade core portion 18 allows a designer to control the overall stiffness and characteristics of the blade 22.
- the cavity 14 containing the blade core portion 18 is typically embedded within the blade shell portion 10. Embedding the cavity 14 enables blades 22 to be produced with similar profiles and dissimilar stiffnesses. For example, because the cavity 14 is embedded in the blade shell portion 10, blades 22 containing the cavity 14 may maintain the same profile as blades 22 not containing a cavity 14. In addition, the size of the cavity 14 may be changed without affecting the profile of the blade 22, provided the cavity 14 remains contained within the blade shell portion 10. Accordingly, a plurality of blades 22 may be disposed upon the rotor disk 30, and the blades 22 may or may not contain the blade core portion 18, as shown in Figure 5. Preferably, a plurality of blades 22 disposed upon the rotor disk 30 comprises alternating the blades 22 with and without the embedded blade core portion 18. The blades 22 have identical profiles and thus improve on the prior art dissimilar profiles, which have undesirable aerodynamic characteristics.
- the blades 22 are ordinarily formed by diffusion bonding; two blade 22 halves are joined under extreme temperatures and pressures.
- a metal matrix composite (MMC) 26 material withstands these extremes.
- the MMC 26 is sandwiched between the two blade 22 halves as the blade 22 halves are bonded together.
- Blades 22 may be made of Ti-6-4, while the MMC 26 may be Ti-6-4 with silicon carbide fiber additive. Varying the amount and orientation of the silicon carbide fiber additive alters the stiffness of the MMC 26. Of course, this invention extends to many other appropriate materials. In addition, stiffness can be varied by varying geometry, etc. Also while an alternate orientation of two different stiffnesses is disclosed, other arrangements of different stiffnesses could be utilized within the scope of this invention.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/200,359 US20070036658A1 (en) | 2005-08-09 | 2005-08-09 | Tunable gas turbine engine fan assembly |
Publications (1)
Publication Number | Publication Date |
---|---|
EP1752610A2 true EP1752610A2 (de) | 2007-02-14 |
Family
ID=37074202
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06254096A Withdrawn EP1752610A2 (de) | 2005-08-09 | 2006-08-04 | Gasturbinenrotor, Gasturbine und Frequenzabstimmungsverfahren für ein Gasturbinenbläser |
Country Status (3)
Country | Link |
---|---|
US (1) | US20070036658A1 (de) |
EP (1) | EP1752610A2 (de) |
JP (1) | JP2007046608A (de) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1985803A1 (de) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln |
GB2490127A (en) * | 2011-04-19 | 2012-10-24 | Rolls Royce Plc | Aerofoil assembly |
WO2013147972A1 (en) * | 2012-01-26 | 2013-10-03 | United Technologies Corporation | Modal tuning for vanes |
WO2014197119A2 (en) | 2013-04-16 | 2014-12-11 | United Technologies Corporation | Rotors with modulus mistuned airfoils |
EP3363993A1 (de) * | 2017-02-20 | 2018-08-22 | Rolls-Royce plc | Lüfter und zugehöriges gasturbinentriebwerk |
US10677259B2 (en) | 2016-05-06 | 2020-06-09 | General Electric Company | Apparatus and system for composite fan blade with fused metal lead edge |
US11668317B2 (en) | 2021-07-09 | 2023-06-06 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
US11674399B2 (en) | 2021-07-07 | 2023-06-13 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9004873B2 (en) | 2010-12-27 | 2015-04-14 | Rolls-Royce Corporation | Airfoil, turbomachine and gas turbine engine |
US8834098B2 (en) | 2011-12-02 | 2014-09-16 | United Technologies Corporation | Detuned vane airfoil assembly |
TWI524840B (zh) | 2012-03-30 | 2016-03-01 | 台達電子工業股份有限公司 | 散熱模組 |
WO2015047511A2 (en) * | 2013-07-15 | 2015-04-02 | United Technologies Corporation | Composite airfoil |
US10400606B2 (en) * | 2014-01-15 | 2019-09-03 | United Technologies Corporation | Mistuned airfoil assemblies |
EP2942481B1 (de) | 2014-05-07 | 2019-03-27 | Rolls-Royce Corporation | Rotor für einen gasturbinenmotor |
US10641281B2 (en) | 2016-08-08 | 2020-05-05 | United Technologies Corporation | Mistuned laminate airfoil |
US11149558B2 (en) | 2018-10-16 | 2021-10-19 | General Electric Company | Frangible gas turbine engine airfoil with layup change |
US11434781B2 (en) | 2018-10-16 | 2022-09-06 | General Electric Company | Frangible gas turbine engine airfoil including an internal cavity |
US10760428B2 (en) | 2018-10-16 | 2020-09-01 | General Electric Company | Frangible gas turbine engine airfoil |
US10746045B2 (en) | 2018-10-16 | 2020-08-18 | General Electric Company | Frangible gas turbine engine airfoil including a retaining member |
US11111815B2 (en) | 2018-10-16 | 2021-09-07 | General Electric Company | Frangible gas turbine engine airfoil with fusion cavities |
US10837286B2 (en) | 2018-10-16 | 2020-11-17 | General Electric Company | Frangible gas turbine engine airfoil with chord reduction |
US12043368B2 (en) | 2022-03-23 | 2024-07-23 | General Electric Company | Rotating airfoil assembly |
US20240280027A1 (en) * | 2023-02-21 | 2024-08-22 | General Electric Company | Turbine engine airfoil with a woven core and woven layer |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3368795A (en) * | 1967-07-12 | 1968-02-13 | Gen Motors Corp | Composite rotor blade having high modal frequencies |
US4098559A (en) * | 1976-07-26 | 1978-07-04 | United Technologies Corporation | Paired blade assembly |
US4097192A (en) * | 1977-01-06 | 1978-06-27 | Curtiss-Wright Corporation | Turbine rotor and blade configuration |
US4178667A (en) * | 1978-03-06 | 1979-12-18 | General Motors Corporation | Method of controlling turbomachine blade flutter |
DE3826378A1 (de) * | 1988-08-03 | 1990-02-08 | Mtu Muenchen Gmbh | Fasertechnische propellerschaufeln |
US5269657A (en) * | 1990-07-20 | 1993-12-14 | Marvin Garfinkle | Aerodynamically-stable airfoil spar |
US5181678A (en) * | 1991-02-04 | 1993-01-26 | Flex Foil Technology, Inc. | Flexible tailored elastic airfoil section |
US5160242A (en) * | 1991-05-31 | 1992-11-03 | Westinghouse Electric Corp. | Freestanding mixed tuned steam turbine blade |
US5490764A (en) * | 1994-05-23 | 1996-02-13 | General Electric Company | Unshrouded blading for high bypass turbofan engines |
WO1998036966A1 (en) * | 1997-02-21 | 1998-08-27 | California Institute Of Technology | Rotors with mistuned blades |
US6190133B1 (en) * | 1998-08-14 | 2001-02-20 | Allison Engine Company | High stiffness airoil and method of manufacture |
US6379112B1 (en) * | 2000-11-04 | 2002-04-30 | United Technologies Corporation | Quadrant rotor mistuning for decreasing vibration |
US6471482B2 (en) * | 2000-11-30 | 2002-10-29 | United Technologies Corporation | Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability |
US6428278B1 (en) * | 2000-12-04 | 2002-08-06 | United Technologies Corporation | Mistuned rotor blade array for passive flutter control |
USH2057H1 (en) * | 2001-01-10 | 2003-01-07 | Sandia Corporation | Load attenuating passively adaptive wind turbine blade |
US7147437B2 (en) * | 2004-08-09 | 2006-12-12 | General Electric Company | Mixed tuned hybrid blade related method |
-
2005
- 2005-08-09 US US11/200,359 patent/US20070036658A1/en not_active Abandoned
-
2006
- 2006-08-04 EP EP06254096A patent/EP1752610A2/de not_active Withdrawn
- 2006-08-07 JP JP2006214059A patent/JP2007046608A/ja active Pending
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1985803A1 (de) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Verfahren zum Herstellen von beschichteten Turbinenlaufschaufeln |
WO2008128902A1 (de) * | 2007-04-23 | 2008-10-30 | Siemens Aktiengesellschaft | Verfahren zum herstellen von beschichteten turbinenlaufschaufeln und laufschaufelring für einen rotor einer axial durchströmten turbine |
US8607455B2 (en) | 2007-04-23 | 2013-12-17 | Siemens Aktiengesellschaft | Method for the production of coated turbine moving blades and moving-blade ring for a rotor of an axial-throughflow turbine |
GB2490127A (en) * | 2011-04-19 | 2012-10-24 | Rolls Royce Plc | Aerofoil assembly |
WO2013147972A1 (en) * | 2012-01-26 | 2013-10-03 | United Technologies Corporation | Modal tuning for vanes |
EP2986822A4 (de) * | 2013-04-16 | 2016-05-18 | United Technologies Corp | Rotoren mit schaufeln mit dejustiertem modul |
WO2014197119A2 (en) | 2013-04-16 | 2014-12-11 | United Technologies Corporation | Rotors with modulus mistuned airfoils |
US10808543B2 (en) | 2013-04-16 | 2020-10-20 | Raytheon Technologies Corporation | Rotors with modulus mistuned airfoils |
US10677259B2 (en) | 2016-05-06 | 2020-06-09 | General Electric Company | Apparatus and system for composite fan blade with fused metal lead edge |
EP3363993A1 (de) * | 2017-02-20 | 2018-08-22 | Rolls-Royce plc | Lüfter und zugehöriges gasturbinentriebwerk |
US10724536B2 (en) | 2017-02-20 | 2020-07-28 | Rolls-Royce Plc | Fan |
US11674399B2 (en) | 2021-07-07 | 2023-06-13 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
US11668317B2 (en) | 2021-07-09 | 2023-06-06 | General Electric Company | Airfoil arrangement for a gas turbine engine utilizing a shape memory alloy |
Also Published As
Publication number | Publication date |
---|---|
JP2007046608A (ja) | 2007-02-22 |
US20070036658A1 (en) | 2007-02-15 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1752610A2 (de) | Gasturbinenrotor, Gasturbine und Frequenzabstimmungsverfahren für ein Gasturbinenbläser | |
US10801519B2 (en) | Blade disk arrangement for blade frequency tuning | |
US9382916B2 (en) | Method for machining an integrally bladed rotor | |
RU2341662C2 (ru) | Турбина турбомашины, оснащенная лопатками с различными резонансными частотами, способ ее изготовления и способ обеспечения заданной резонансной частоты лопатки турбины | |
JP5322398B2 (ja) | タービンバケット内の応力を低減するための方法及びタービンブレード | |
EP1826414B1 (de) | Rotorblatt für die zweite Phase eines Kompressors | |
US20050249586A1 (en) | Method for introducing a deliberate mismatch on a turbomachine bladed wheel, bladed wheel with a deliberate mismatch | |
EP1754859B1 (de) | Verfahren und Vorrichtung zur Reduktion von induzierten Schaufelschwingungen | |
GB2490127A (en) | Aerofoil assembly | |
JP2007270839A (ja) | 非金属製充填材を空洞部に機械的に保持するタービンブレード | |
US9546552B2 (en) | Gas turbine | |
WO2013147972A1 (en) | Modal tuning for vanes | |
EP1217171A2 (de) | Verstärkungsrippe zur Beeinflussung der Eigenfrequenz einer Turbinenschaufel | |
EP1234949B1 (de) | Kühllufteinlässe im Fusse eines Schaufelblattes | |
CA2464249A1 (en) | Methods and apparatus for structurally supporting airfoil tips | |
EP3456921B1 (de) | Verdichterrotor mit beschichteten schaufeln | |
EP3085893A1 (de) | Verstimmter gasturbinenmotorrotors | |
EP1217170A2 (de) | Methode um die Eigenfrequenz von Turbinenschaufeln durch die Orientierung der sekundären Kristallachsen zu beeinflussen | |
US10641112B2 (en) | Bladed disk | |
EP2942484A1 (de) | Schaufelelement mit querstrebe | |
EP3430239B1 (de) | Schaufel für eine gasturbine mit einem oder mehreren gekapselten hohlräumen | |
JPH04232305A (ja) | 蒸気タービン用回転羽根及びその形成方法 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK YU |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN |
|
18W | Application withdrawn |
Effective date: 20081105 |