US1554614A - Turbine blading - Google Patents
Turbine blading Download PDFInfo
- Publication number
- US1554614A US1554614A US588069A US58806922A US1554614A US 1554614 A US1554614 A US 1554614A US 588069 A US588069 A US 588069A US 58806922 A US58806922 A US 58806922A US 1554614 A US1554614 A US 1554614A
- Authority
- US
- United States
- Prior art keywords
- elements
- wedge
- blade
- blades
- blading
- 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.)
- Expired - Lifetime
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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
-
- 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
- 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
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- Y10S415/00—Rotary kinetic fluid motors or pumps
- Y10S415/91—Reversible between pump and motor use
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
-
- 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
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
Definitions
- My invention relates to turbine blades having lateral projections which define shrouds or deck partitions and it has for 1ts object to provide wedge members in connection with the projections which shall assure the maintenance of a tight shroud or part-1- tion at all times, thereby limiting blade vibration, and in particular which shall per mit of compensating movements taking place when the rotor and blading undergo disproportionate deformation.
- FIG. 1 is a fragmentary detail view showing a plurality of blades of a row with my tightening wedges applied thereto:
- Fig. 2 is a sectional view taken along the line IIII of Fig. 1;
- Fig. 3 is a detail View, similar to Fig. 1. but showing blade elements carried, by the tightening wedges:
- Fig. 4 is a detail view, similar to Fig. 3, but having a different type of means for limiting inward movement of the wedge and blade elements;
- Fig. 5 is a face view of the blading shown in Fig. 4;
- Fig. 1 is a fragmentary detail view showing a plurality of blades of a row with my tightening wedges applied thereto:
- Fig. 2 is a sectional view taken along the line IIII of Fig. 1;
- Fig. 3 is a detail View, similar to Fig. 1. but showing blade elements carried, by the tightening wedges:
- Fig. 4 is a detail
- FIG. 6 is a detail view showing my tightening wedge mechanism applied to blade tip shrouding
- Fig. 7 is a detail view showing a modified form of shroud and wedge construction
- Fig. 8 is a diagrammatic view illustrating a feature of my invention.
- I show a plurality of blades 10 of a row.
- intermediate abutments or shroud elements 11 which serve to brace the blades and to define inner and outer decks of blade elements 12 and 13.
- the shroud elements 11 are provided with inclined and complementary recesses 14 which define outwardly-converging spaces to receive wedge elements 15.
- The, angle of inclination of the recesses and of the wedges is greater than the angle of rest for a purpose to be described.
- Any suitable means may be provided for limiting inward movement of the wedges 15 after they are assembled: for example, in Fig. 1, I show spring elements 16, carried on the inner sides of shroud elements 11 for this purpose.
- the angle of inclination of the faces thereof is greater than the angle of rest.
- the springs 16, or any suitable equivalent thereof serve The above mentioned action is best illus- I trated by reference to Fig. 8 in which the 100. g of the wedges so shroud elements 11 and wedge 15 are shown drawn to a larger scale; In the drawing, the angle of the surface .of the wedge 15 and the shroud elements 11 is indicated at b, the angle of'rest at c and an angle smaller than the angle of rest at a. If.
- the angle of the surface of the wedge 15 and the shroud element 11 were equal to the angle a it is obvious that when the blading expands and the wedge is moved outwardly by centrifugal force, assuming a new position, it will remain in the new position upon contraction of the blading, entailing crushdefined bythe inclined recesses 14 and which 4 carry blade elements 18 interposed between the outer deck blade elements 13.
- the blade elements 18 are preferably smaller than the outer deck blade elements 13, and they serve the double purpose of increasing the effective mass subject to centrifugal force to urge the wedge elements 17 tightly in place between the shroud elements 11 and of. abstracting energy the upper deck.
- Fig. 3 I show springs 19 connected to the outer deck blade elements 13 and to the wedge-carried blade elements 18 for the pur pose of limiting inward movement of the wedges 17 and the blade elementscarrie thereby.
- Fig. 5 I show a different means for limiting inward movement of the wedges 17 and the blade elements 18 carried thereby.
- the root of the blade portion 18 overhangs the shroud elements 11 and caulking 20 is inserted therebetween.
- the caulking will give sufiiciently to provide for the necessary clearance for movement of the wedge elements 17 in order to limit vibration of the blades.
- Fig. 6 I show wedge elements 21 which are interposed between the shroud elements 22 arranged at the tips of the blades 23,
- FIG.- 7 I show a modified form'of shroud constructon which may be used in any of the modifications heretofore described.
- each blade element 25 provided with a single shroud or partition element 26, having an inclined recess 27 to receive wedge 28 which fits in the recess and against an adjacent blade in order to maintain a tight shroudin I vl from motive fluid passing through.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Sept. 22, 1925.
R. C. ALLEN TURBINE BLADING Filed Sept. 13. 1922 INVENTOR ATT NEY Patented Sept. 22, 1925. I
UNITED STATES ROBERT C. ALLEN, OF ESSINGTON, PENNSYLVANIA, ASSIGNOR TO WESTINGHOUSE ELECTRIC AND MANUFACTURING COMPANY, A CORPORATION OF PENNSYLVANIA.
rename BLADING.
To all whom it may concern.
Be it known that I, Ronnn'r C. ALLEN, a citizen of the United States, and a resident of Essington, in the county of Delaware and State of Pennsylvania, have invented a new and useful Improvement in Turbine Bladlng, of which the following is a specification.
My invention relates to turbine blades having lateral projections which define shrouds or deck partitions and it has for 1ts object to provide wedge members in connection with the projections which shall assure the maintenance of a tight shroud or part-1- tion at all times, thereby limiting blade vibration, and in particular which shall per mit of compensating movements taking place when the rotor and blading undergo disproportionate deformation.
A further object of my invention 1s to provide wedge elements of the character referred to with blade elements which shall serve the double purpose of increasing the mass which is effective under centrifugal force to maintain the wedge elements tight and of abstracting energy from motive fluid passing through the blading.
Apparatus embodying features of my 1nvention is illustrated in the accompanying drawings, forming a part of this application, in which Fig. 1 is a fragmentary detail view showing a plurality of blades of a row with my tightening wedges applied thereto: Fig. 2 is a sectional view taken along the line IIII of Fig. 1; Fig. 3 is a detail View, similar to Fig. 1. but showing blade elements carried, by the tightening wedges: Fig. 4 is a detail view, similar to Fig. 3, but having a different type of means for limiting inward movement of the wedge and blade elements; Fig. 5 is a face view of the blading shown in Fig. 4; Fig. 6 is a detail view showing my tightening wedge mechanism applied to blade tip shrouding; Fig. 7 is a detail view showing a modified form of shroud and wedge construction; and Fig. 8 is a diagrammatic view illustrating a feature of my invention. J
With turbine blading having shrouds or partitions, more particularly with relatively tall blading, difi'iculty has been encountered due to crushing or ruinous deformation of the shroud or partition elements taking place in consequence of disproportionate or unequal rates of expansion of the rotor and of the blading. When steam is turned on. in
to limit inward movement quired by the physical condition of the blad ing and the spindle.
Referring'now to the drawings for a more detailed descrlption of my invention, in Fig.
1, I show a plurality of blades 10 of a row.
provided with intermediate abutments or shroud elements 11 which serve to brace the blades and to define inner and outer decks of blade elements 12 and 13.
The shroud elements 11 are provided with inclined and complementary recesses 14 which define outwardly-converging spaces to receive wedge elements 15. The, angle of inclination of the recesses and of the wedges is greater than the angle of rest for a purpose to be described. Any suitable means may be provided for limiting inward movement of the wedges 15 after they are assembled: for example, in Fig. 1, I show spring elements 16, carried on the inner sides of shroud elements 11 for this purpose.
With the assembly of blading and wedge elements of this type, should expansion of the bladingtake place in operation, due to any cause, the wedge elements 16 will move out under the influence of centrifugal force to maintain a tight fit in the recesses, thereby serving to provide a firm bracing structure for the blades at all times. In thisway, vibration of the blades, permitted by the shroud elements becoming spaced apart due to expansion or stretching of the blades, is avoided. On the other hand, with a contraction of the blade structure, the wedge elements 16 move inwardly due to the fact that i 1,554,614. PATENT OFFICE..-
the angle of inclination of the faces thereof is greater than the angle of rest. The springs 16, or any suitable equivalent thereof serve The above mentioned action is best illus- I trated by reference to Fig. 8 in which the 100. g of the wedges so shroud elements 11 and wedge 15 are shown drawn to a larger scale; In the drawing, the angle of the surface .of the wedge 15 and the shroud elements 11 is indicated at b, the angle of'rest at c and an angle smaller than the angle of rest at a. If.
the angle of the surface of the wedge 15 and the shroud element 11 were equal to the angle a it is obvious that when the blading expands and the wedge is moved outwardly by centrifugal force, assuming a new position, it will remain in the new position upon contraction of the blading, entailing crushdefined bythe inclined recesses 14 and which 4 carry blade elements 18 interposed between the outer deck blade elements 13. r The blade elements 18 are preferably smaller than the outer deck blade elements 13, and they serve the double purpose of increasing the effective mass subject to centrifugal force to urge the wedge elements 17 tightly in place between the shroud elements 11 and of. abstracting energy the upper deck.
In Fig. 3, I show springs 19 connected to the outer deck blade elements 13 and to the wedge-carried blade elements 18 for the pur pose of limiting inward movement of the wedges 17 and the blade elementscarrie thereby.
In Fig. 5, I show a different means for limiting inward movement of the wedges 17 and the blade elements 18 carried thereby. In this view, the root of the blade portion 18 overhangs the shroud elements 11 and caulking 20 is inserted therebetween. In operation. the caulking will give sufiiciently to provide for the necessary clearance for movement of the wedge elements 17 in order to limit vibration of the blades.
In Fig. 6, I show wedge elements 21 which are interposed between the shroud elements 22 arranged at the tips of the blades 23,
inward movement of the wedge elements 21 being limited by any suitable means, such as by springs 24. The wedge construction shown in this view operates similarly to that shown in Fig. 1, already referredto.
In Fig.- 7, I show a modified form'of shroud constructon which may be used in any of the modifications heretofore described. In this view, I show each blade element 25 provided with a single shroud or partition element 26, having an inclined recess 27 to receive wedge 28 which fits in the recess and against an adjacent blade in order to maintain a tight shroudin I vl from motive fluid passing through.
From the foregoing, it will be apparent that I have -devised shrouding for turbine blades which is-particularly useful in connection with tall blading and which shrouding is maintained automatically tight at all times to limit vibration, regardless of any stretching of the blades or disproportionate expansion of the blades and the rotor, in order to limit vibration.
While I have shown my invention in bu five forms, it will be obvious to those skilled in the art that it is not 'so limited, but is susceptible of various other changes and modifications without departing from the spirit thereof, and I desire, therefore, that only such limitations shall be placed thereupon as are imposed by the prior art or as are specifically set forth in the appended claims.
What I claim is 1. The combination of a row of turbine blades, shrouding members between adjacent blades in a row, said members having opposed and abutting faces provided with seats, one of which is inclined, and a wedge fitting the seats.
2. The combination of a row of turbine blades, bracing means between adjacent blades in a row, said bracing means having opposed faces provided with inclined seats,
and outwardy-tapering wedges fitting the seats. I v
3. The combination of a row of turbine blades, bracing means for the blades, and outwardly-tapering wedge means cooperating with the bracing means to keep the blading tight, the angle of inclination of thewedge faces being greater than the angle cf rest.
4. The combination of a row of turbine blades having bracing members between adjacent blades, said members having lateral and inclined seats defining outwardly-converging spaces and wedges fitting the spaces.
5. The combination of a row of turbine blades having bracing members between adjaoent blades, said members having lateral and inclined seats defining outwardly-converging spaces, wedges in the spaces, and means for limiting inward movement of the wedges.
6. The combination of a row' of turbine blades, intermediate and laterally-extending deck members on the blades defining inner and outer decks of blade portions and provided with inclined faces which define outwardly-converging spaces, and wedge members in the spaces.
7. The combination of a row of decked turbine blades having deck-defining mem- 8. The combination of a'row of blade elements, intermediate projections on the blade elements having inclined seats which define outwardly-converging spaces, wedge clementsin the seats and fitting the spaces, and means cooperating with the wedge elements for limiting inward movement thereof.
9. The combination of a row of'blade elements. intermediate projections on the blade elements defining inner and outer decks of blade portions and provided with opposed and inclined recesses defining outwardly-converging spaces. wedge elements fittingthe spaces, and blade elements carried by the thin ends of the wedge elements and interposed between the outer deck blade portions.
10. The combination of a row of blade elements. intermediate projections on the blade elements defining inner and outer decks of blade portions and provided with opposed and inclined recesses defining outwardly-converging spaces, wedge elements fitting the spaces, blade elements carried by the thin ends of the Wedge elements and interposed between the outer deck blade portions, and means cooperating with the latter blade elements for limiting inward movement of the wedge elements.
11. The combination of a row of blade elements, intermediate projections on the blade"'l'ements defining inner and outer decks of blade portions and provided with opposed and inclined recesses defining outwardly-converging spaces. wedge elements fitting the spaces. blade elementscarried by the thin ends of the wedge elements and interposed between the outer deck blade portions. the latter blade elements extending beyond the lateral edges of the wedge elements over the sides of the projections. and caulking means cooperating with the latter blade elements and with the projections for limiting inward movement of the wedge elements.
In testimom whereof. I have hereunto subscribed my name this 7th day of September,1922.
ROBERT C. ALLEN.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US588069A US1554614A (en) | 1922-09-13 | 1922-09-13 | Turbine blading |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US588069A US1554614A (en) | 1922-09-13 | 1922-09-13 | Turbine blading |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US1554614A true US1554614A (en) | 1925-09-22 |
Family
ID=24352348
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US588069A Expired - Lifetime US1554614A (en) | 1922-09-13 | 1922-09-13 | Turbine blading |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US1554614A (en) |
Cited By (34)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2454115A (en) * | 1945-04-02 | 1948-11-16 | Allis Chalmers Mfg Co | Turbine blading |
| US2660400A (en) * | 1948-11-25 | 1953-11-24 | Rolls Royce | Blade for turbines or compressors |
| US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
| US2920864A (en) * | 1956-05-14 | 1960-01-12 | United Aircraft Corp | Secondary flow reducer |
| US2936155A (en) * | 1951-12-10 | 1960-05-10 | Power Jets Res & Dev Ltd | Resiliently mounted turbine blades |
| US2942843A (en) * | 1956-06-15 | 1960-06-28 | Westinghouse Electric Corp | Blade vibration damping structure |
| US2999631A (en) * | 1958-09-05 | 1961-09-12 | Gen Electric | Dual airfoil |
| US3020386A (en) * | 1959-06-10 | 1962-02-06 | Naxon Irving | Electric heaters |
| DE1212108B (en) * | 1962-07-11 | 1966-03-10 | Gen Electric | Single-edged axial flow machine impeller |
| US3396905A (en) * | 1966-09-28 | 1968-08-13 | Gen Motors Corp | Ducted fan |
| US3751182A (en) * | 1971-08-20 | 1973-08-07 | Westinghouse Electric Corp | Guide vanes for supersonic turbine blades |
| US3752599A (en) * | 1971-03-29 | 1973-08-14 | Gen Electric | Bucket vibration damping device |
| US3837761A (en) * | 1971-08-20 | 1974-09-24 | Westinghouse Electric Corp | Guide vanes for supersonic turbine blades |
| US3990813A (en) * | 1973-11-30 | 1976-11-09 | Hitachi, Ltd. | Apparatus for tying moving blades |
| US4111603A (en) * | 1976-05-17 | 1978-09-05 | Westinghouse Electric Corp. | Ceramic rotor blade assembly for a gas turbine engine |
| US4183720A (en) * | 1978-01-03 | 1980-01-15 | The United States Of America As Represented By The Secretary Of The Air Force | Composite fan blade platform double wedge centrifugal seal |
| US4257742A (en) * | 1978-04-03 | 1981-03-24 | Tokyo Shibaura Denki Kabushiki Kaisha | Device for interconnecting turbine blades |
| US4497611A (en) * | 1982-03-25 | 1985-02-05 | Kraftwerk Union Aktiengesellschaft | Device for vibration damping in a guide vane ring |
| US4936749A (en) * | 1988-12-21 | 1990-06-26 | General Electric Company | Blade-to-blade vibration damper |
| US4986737A (en) * | 1988-12-29 | 1991-01-22 | General Electric Company | Damped gas turbine engine airfoil row |
| US5146679A (en) * | 1991-01-16 | 1992-09-15 | Ortolano Ralph J | Method of converting grouped blading to equivalent integral covered blading |
| US5156528A (en) * | 1991-04-19 | 1992-10-20 | General Electric Company | Vibration damping of gas turbine engine buckets |
| US5226784A (en) * | 1991-02-11 | 1993-07-13 | General Electric Company | Blade damper |
| US5238368A (en) * | 1991-01-16 | 1993-08-24 | Ortolano Ralph J | Converting grouped blading to equivalent integral covered blading |
| US5261790A (en) * | 1992-02-03 | 1993-11-16 | General Electric Company | Retention device for turbine blade damper |
| US5302085A (en) * | 1992-02-03 | 1994-04-12 | General Electric Company | Turbine blade damper |
| EP0702131A1 (en) * | 1994-09-19 | 1996-03-20 | General Electric Company | Stable blade vibration damper for gas turbine engine |
| US20020146322A1 (en) * | 2001-04-10 | 2002-10-10 | Stuart Yeo | Vibration damping |
| US20050241149A1 (en) * | 2002-08-14 | 2005-11-03 | Volvo Aero Corporation | Method for manufacturing a stator component |
| US7572098B1 (en) * | 2006-10-10 | 2009-08-11 | Johnson Gabriel L | Vane ring with a damper |
| US20120201684A1 (en) * | 2011-02-08 | 2012-08-09 | Andy Turko | Mate face brazing for turbine components |
| US20180163556A1 (en) * | 2016-12-12 | 2018-06-14 | Safran Aircraft Engines | Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine |
| US20180274381A1 (en) * | 2017-03-23 | 2018-09-27 | General Electric Company | Gas turbine engine component incorporating a seal slot |
| US11149552B2 (en) | 2019-12-13 | 2021-10-19 | General Electric Company | Shroud for splitter and rotor airfoils of a fan for a gas turbine engine |
-
1922
- 1922-09-13 US US588069A patent/US1554614A/en not_active Expired - Lifetime
Cited By (39)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2454115A (en) * | 1945-04-02 | 1948-11-16 | Allis Chalmers Mfg Co | Turbine blading |
| US2660400A (en) * | 1948-11-25 | 1953-11-24 | Rolls Royce | Blade for turbines or compressors |
| US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
| US2936155A (en) * | 1951-12-10 | 1960-05-10 | Power Jets Res & Dev Ltd | Resiliently mounted turbine blades |
| US2920864A (en) * | 1956-05-14 | 1960-01-12 | United Aircraft Corp | Secondary flow reducer |
| US2942843A (en) * | 1956-06-15 | 1960-06-28 | Westinghouse Electric Corp | Blade vibration damping structure |
| US2999631A (en) * | 1958-09-05 | 1961-09-12 | Gen Electric | Dual airfoil |
| US3020386A (en) * | 1959-06-10 | 1962-02-06 | Naxon Irving | Electric heaters |
| DE1212108B (en) * | 1962-07-11 | 1966-03-10 | Gen Electric | Single-edged axial flow machine impeller |
| US3396905A (en) * | 1966-09-28 | 1968-08-13 | Gen Motors Corp | Ducted fan |
| US3752599A (en) * | 1971-03-29 | 1973-08-14 | Gen Electric | Bucket vibration damping device |
| US3751182A (en) * | 1971-08-20 | 1973-08-07 | Westinghouse Electric Corp | Guide vanes for supersonic turbine blades |
| US3837761A (en) * | 1971-08-20 | 1974-09-24 | Westinghouse Electric Corp | Guide vanes for supersonic turbine blades |
| US3990813A (en) * | 1973-11-30 | 1976-11-09 | Hitachi, Ltd. | Apparatus for tying moving blades |
| US4111603A (en) * | 1976-05-17 | 1978-09-05 | Westinghouse Electric Corp. | Ceramic rotor blade assembly for a gas turbine engine |
| US4183720A (en) * | 1978-01-03 | 1980-01-15 | The United States Of America As Represented By The Secretary Of The Air Force | Composite fan blade platform double wedge centrifugal seal |
| US4257742A (en) * | 1978-04-03 | 1981-03-24 | Tokyo Shibaura Denki Kabushiki Kaisha | Device for interconnecting turbine blades |
| US4497611A (en) * | 1982-03-25 | 1985-02-05 | Kraftwerk Union Aktiengesellschaft | Device for vibration damping in a guide vane ring |
| US4936749A (en) * | 1988-12-21 | 1990-06-26 | General Electric Company | Blade-to-blade vibration damper |
| US4986737A (en) * | 1988-12-29 | 1991-01-22 | General Electric Company | Damped gas turbine engine airfoil row |
| US5146679A (en) * | 1991-01-16 | 1992-09-15 | Ortolano Ralph J | Method of converting grouped blading to equivalent integral covered blading |
| US5238368A (en) * | 1991-01-16 | 1993-08-24 | Ortolano Ralph J | Converting grouped blading to equivalent integral covered blading |
| US5226784A (en) * | 1991-02-11 | 1993-07-13 | General Electric Company | Blade damper |
| US5156528A (en) * | 1991-04-19 | 1992-10-20 | General Electric Company | Vibration damping of gas turbine engine buckets |
| US5261790A (en) * | 1992-02-03 | 1993-11-16 | General Electric Company | Retention device for turbine blade damper |
| US5302085A (en) * | 1992-02-03 | 1994-04-12 | General Electric Company | Turbine blade damper |
| US5369882A (en) * | 1992-02-03 | 1994-12-06 | General Electric Company | Turbine blade damper |
| EP0702131A1 (en) * | 1994-09-19 | 1996-03-20 | General Electric Company | Stable blade vibration damper for gas turbine engine |
| US6659725B2 (en) * | 2001-04-10 | 2003-12-09 | Rolls-Royce Plc | Vibration damping |
| US20020146322A1 (en) * | 2001-04-10 | 2002-10-10 | Stuart Yeo | Vibration damping |
| US20050241149A1 (en) * | 2002-08-14 | 2005-11-03 | Volvo Aero Corporation | Method for manufacturing a stator component |
| US7572098B1 (en) * | 2006-10-10 | 2009-08-11 | Johnson Gabriel L | Vane ring with a damper |
| US20120201684A1 (en) * | 2011-02-08 | 2012-08-09 | Andy Turko | Mate face brazing for turbine components |
| US9610644B2 (en) * | 2011-02-08 | 2017-04-04 | United Technologies Corporation | Mate face brazing for turbine components |
| US20180163556A1 (en) * | 2016-12-12 | 2018-06-14 | Safran Aircraft Engines | Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine |
| US11053810B2 (en) * | 2016-12-12 | 2021-07-06 | Safran Aircraft Engines | Assembly of turbine engine parts comprising a fan blade having an integrated platform, and corresponding turbine engine |
| US20180274381A1 (en) * | 2017-03-23 | 2018-09-27 | General Electric Company | Gas turbine engine component incorporating a seal slot |
| US10941671B2 (en) * | 2017-03-23 | 2021-03-09 | General Electric Company | Gas turbine engine component incorporating a seal slot |
| US11149552B2 (en) | 2019-12-13 | 2021-10-19 | General Electric Company | Shroud for splitter and rotor airfoils of a fan for a gas turbine engine |
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