US3117716A - Ducted rotor - Google Patents
Ducted rotor Download PDFInfo
- Publication number
- US3117716A US3117716A US272141A US27214163A US3117716A US 3117716 A US3117716 A US 3117716A US 272141 A US272141 A US 272141A US 27214163 A US27214163 A US 27214163A US 3117716 A US3117716 A US 3117716A
- Authority
- US
- United States
- Prior art keywords
- shroud
- blade
- shoe
- end portion
- air
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
Definitions
- a fan blade rotatably mounted concentrically within said shroud and having an end portion terminating closely adjacent to but spaced from the inner surface of said shroud
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
1964 R. K. WERNICKE 3,117,716
DUCTED ROTOR Filed April 10, 1963 INVENTOR. RODNEY K- WEP/V/CK! AT TOPN E Y5 v United States Patent 3,117,716 DUCTED ROTOR Rodney K. Wernicke, Hurst, Tern, assignor to Bell Aerospace Corporation, Wheatfield, N.Y. Filed Apr. 10, 1963, Ser. No. 272,141 7 Claims. ((31. 230-120) This invention relates to ducted propellers, fans, or the like; and more particularly to means for improving the efiiciency of operation thereof.
Whereas it is well known that for maximum efficiency a ducted propeller or fan or the like must operate with minimum blade tip clearance relative to its shroud, due to inequalities of manufacture and typical hazards of usage it has heretofore been requisite to provide an undesirably large gap between the blade tip path and the wall of the enclosing duct in order to insure against accidental collision and/or undesirable frictional contact therebetween.
It is an object of the present invention to provide an improved form of blade for propellers or fans or other rotor arrangements when used in ducted systems, whereby the blade may operate with safety substantially closer to the duct Wall, compared to prior ducted rotor arrangements.
Another object is to provide an improved device as aforesaid an improved rotor blade tip construction whereby the blade tip path automatically adjusts relative to the duct wall to provide minimum clearance therebetween. Another object is to provide an improved blade construction including a floating blade tip shoe which automatically moves into close-fitting relation with the enveloping duct, while at the same time rictional contacts therebetween are precluded.
Other objects and advantages of the invention will appear from the specification hereinafter and in the accompanying drawings, wherein:
FIG. 1 is a fragmentary plan view of a rotor blade and an associated duct or cowling, embodying the features of the present invention;
FIG. 2 is a fragmentary front edge view of the device in FIG. 1;
FIG. 3 is an enlarged scale plan view corresponding to a portion of FIG. 1, but showing a modified arrangement of the invention;
FIG. 4 is a fragmentary front edge view of the device of FIG. 3; and
FIG. 5 is an end view of the rotor blade tip arrangement of FIGS. 3, 4.
FIGS. 1-2 illustrate an embodiment of the invention in connection with a ducted rotor system including a cylindrical duct Within which is rotating a rotor blade designated generally at 12 and arranged to be driven as by means of a rotor shaft 14. The direction of rotation of the blade 12 is indicated by the arrow in FIG. 1. In accord with the present invention the blade tip and portion is hollowed as indicated at 16 to receive in telescopic fitting relation therein a shoe 18 which is generally profiled at its end face to complement the curvature of the cowling 10. In one form of the invention however, as shown in FIGS. l2, the end face 20 of the shoe 18 is curved adjacent its leading edge on a sharper radius than the curve of the cowling 10, so that the leading end portion of the shoe is disposed further away from the cowling 10 than are the main body portions of the shoe. Thus, as the blade swings inside the cowling 10 a quantity of air will be entrapped by the funnel-shaped opening formed between the leading end of the shoe 18 and the cowling 10, and is compressed into the form of an air film upon which the shoe rides as the blade rotates, instead of sliding against the cowling 10.
It will of course be understood that centrifugal forces,
"ice
due to rotation of the blade, will automatically bias the shoe 18 outwardly toward the cowling; but, as explained hereinabove, the film of air entrapped between the shoe and the cowling will preclude any actual contact therebetween. As shown in FIG. 2, the end face of the shoe 18 at the leading edge thereof may be concave-shaped, as indicated at 22; to enhance the entrapment of air between the shoe and the cowling wall for the purpose explained hereinabove.
FIGS. 35 illustrate a modified form of blade shoe arrangement wherein a tension spring as indicated at 25 is provided to assist the film of entrapped air to maintain the shoe in minutely spaced relation from the cowl surface, against the action of centrifugal forces imposed upon the shoe as the blade rotates. In addition, the spring acts to retract the shoe into the blade when the blade is not rotating. FIGS. 3-5 also illustrate other arrangements for mounting the shoe on the blade and for creating the desired air cushion bet een the cowling wall and the blade shoe. Thus, in this case the shoe is illustrated to be of open end form, and mounted and guided to float relative to the main blade structure by means of pins 28, 30 slidably fitting telescopically in openings formed in the blade structure.
In lieu of forming the leading edge of the blade shoe in funnel-like manner to entrap air as shown in FIGS. 3-5, a ram air inlet opening 26 may be provided in the leading edge of the blade to extend inwardly therefrom and then into communication with a spanwise directed channel 32. The opening for the mounting pin 28 and the air inlet channel 32 may be coincident; for example, the mounting pin 28 may be hollowed to convey the ram air, or a totally separate opening may be employed as preferred. in any case the ram air is thus directed to flow into the interior of the shoe 13 by reason of the air ram and/or centrifugal pumping action, to form a cushion of compressed air between the shoe and the duct wall 14), thereby permitting the overall blade tip structure to follow a path of minimum clearance with the shroud as explained hereinabove.
The blade tip extension or shoe member is preferably formed of some lightweight material such as Teflon or some other suitable plastic material having a low coefficient of friction, because during periods when the propeller is not running at full speed there may be temporary surface contacts between the shoe and the shroud.
It will of course be appreciated that whereas only a few forms of the invention have been illustrated and described in detail by way of example herein, various changes may be made therein without departing from the spirit of the invention or the scope of the following claims.
I claim:
1. A ducted fan assembly comprising, in combination,
a cylindrical shroud,
a fan blade rotatably mounted concentrically within said shroud and having an end portion terminating closely adjacent to but spaced from the inner surface of said shroud,
said end portion of the blade having a recess therein opening toward said inner surface of the shroud,
a shoe device slidably received in said recess for movement beyond said end portion of the blade toward contact with the inner surface of said shrorud under the influence o-f centrifugal force effected by rotation of said blade,
means for rotating said blade in a predetermined direction,
said shoe having an arcuate outer end face of substantially the same radius of curvature as the inner surface of said shroud,
and means for forming a cushion of air bet-ween said shoe and said inner surface of the shroud to maintain 6 said shoe out of contact with such inner surface of the shroud,
said means comprising a leading edge outer end face of said shoe which is of lesser radius of curvature than said inner surface of the shroud.
2. A ducted fan assembly comprising, in combination,
a cylindrical shroud,
a fan blade rotatably mounted concentrically within said shroud and having an end portion terminating closely adjacent to but spaced from the inner surface of said shroud,
said end portion of the blade having a recess therein opening toward said inner surface of the shroud,
a shoe device slidably received in said recess for movement beyond said end portion of the blade toward contact with the inner surface of said shroud under the influence of centrifugal force effected by rotation of said blade,
means for rotating said blade,
said shoe having an arcuate outer end face of substantially the same radius of curvature as the inner surface of said shroud,
means for forming a cushion of air between said shoe and said inner surface of the shroud to maintain said shoe out of contact with such inner surface of the shroud,
and means for mounting said shoe within said blade and resiliently resisting outward movement of said shoe.
3. The assembly as defined in claim 2, wherein said shoe is hollow and provided with an opening at said outer end face thereof,
said means for forming a cushion of air comprising duct means extending from the leading edge of said blade into the hollow interior of said shoe.
4. The assembly as defined in claim 3, wherein said duct means includes a guide pin carried by said shoe and extending radially inwardly therefrom into telescoping relation with said blade.
5. A ducted fan assembly comprising, in combination,
a cylindrical shroud,
a fan blade rotatably mounted concentrically within said shroud and having an end portion terminating closely adjacent to but spaced from the inner surface of said shroud,
said end portion of the blade having a recess therein opening toward said inner surface of the shroud,
a shoe device slidably received in said recess for movement beyond said end portion of the blade toward contact with the inner surface of said shroud under the influence of centrifugal force effected by rotation of said blade,
means for rotating said blade,
said shoe having an arcuate outer end face of substantially the same radius of curvature as the inner surface of said shroud and being recessed inwardly from said outer end face to provide a pocket opposed to said inner face of the shroud,
and duct means extending from the leading edge of said blade to said pocket to build up a cushion of superatmospheric air therein to maintain said shoe out of contact with the inner surface of said shroud.
6. The assembly as defined in claim 5 wherein said duct means includes a hollow guide pin projecting radially inwardly from said shoe and telescopically, slidably received in said blade.
7. A-ducted fan assembly comprising, in combination,
a cylindrical shroud,
a fan blade rotatably mounted concentrically within said shroud and having an end portion terminating closely adjacent to but spaced from the inner surface of said shroud,
said end portion of the blade having a recess therein opening toward said inner surface of the shroud,
a shoe device slidably received in said recess for movement beyond said end portion of the blade toward contact with the inner surface of said shroud under the influence of centrifugal force effected by rotation of said blade,
means for rotating said blade so as to urge said shoe radially outwardly toward said inner surface of said shroud,
and said shoe including means cooperative with said inner surface of said shroud for building up and maintaining a cushioning film of air between said shoe and such inner surface of the shroud.
References Cited in the file of this patent UNITED STATES PATENTS 625,182 Mason May 16, 1899 2,776,107 Willi Jan. 1, 1957 2,814,512 Quinn et al Nov. 26, 1957 2,857,150 Sharp Oct. 21, 1958 FOREIGN PATENTS 389,793 Germany Feb. 7, 1924 446,821 France Oct. 11, 1912
Claims (1)
1. A DUCTED FAN ASSEMBLY COMPRISING, IN COMBINATION, A CYLINDRICAL SHROUD, A FAN BLADE ROTABLY MOUNTED CONCENTRICALLY WITHIN SAID SHROUD AND HAVING AN END PORTION TERMINATING CLOSELY ADJACENT TO BUT SPACED FROM THE INNER SURFACE OF SAID SHROUD, SAID END PORTION OF THE BLADE HAVING A RECESS THEREIN OPENING TOWARD SAID INNER SURFACE OF THE SHROUD, A SHOE DEVICE SLIDABLY RECEIVED IN SAID RECESS FOR MOVEMENT BEYOND SAID END PORTION OF THE BLADE TOWARD CONTACT WITH THE INNER SURFACE OF SAID SHROUD UNDER THE INFLUENCE OF CENTRIFUGAL FORCE EFFECTED BY ROTATION OF SAID BLADE, MEANS FOR ROTATING SAID BLADE IN A PREDETERMINED DIRECTION, SAID SHOE HAVING AN ARCUATE OUTER END FACE OF SUBSTANTIALLY THE SAME RADIUS OF CURVATURE AS THE INNER SUREFACE OF SAID SHROUD, AND MEANS FOR FORMING A CUSHION OF AIR BETWEEN SAID SHOE AND SAID INNER SURFACE OF THE SHROUD TO MAINTAIN SAID SHOE OUT OF CONTACT WITH SUCH INNER SURFACE OF THE SHROUD, SAID MEANS COMPRISING A LEADING EDGE OUTER END FACE OF SAID SHOE WHICH IS OF LESSER RADIUS OF CURVATURE THAN SAID INNER SURFACE OF THE SHROUD.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US272141A US3117716A (en) | 1963-04-10 | 1963-04-10 | Ducted rotor |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US272141A US3117716A (en) | 1963-04-10 | 1963-04-10 | Ducted rotor |
Publications (1)
Publication Number | Publication Date |
---|---|
US3117716A true US3117716A (en) | 1964-01-14 |
Family
ID=23038595
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US272141A Expired - Lifetime US3117716A (en) | 1963-04-10 | 1963-04-10 | Ducted rotor |
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US (1) | US3117716A (en) |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3938906A (en) * | 1974-10-07 | 1976-02-17 | Westinghouse Electric Corporation | Slidable stator seal |
FR2413418A1 (en) * | 1978-10-09 | 1979-07-27 | Diamond Shamrock Corp | PTFE-reinforced fluoro-polymer ion-exchange membrane - for cells producing chlorine and highly conc. alkali hydroxide |
US4169692A (en) * | 1974-12-13 | 1979-10-02 | General Electric Company | Variable area turbine nozzle and means for sealing same |
US4193738A (en) * | 1977-09-19 | 1980-03-18 | General Electric Company | Floating seal for a variable area turbine nozzle |
US4411594A (en) * | 1979-06-30 | 1983-10-25 | Rolls-Royce Limited | Support member and a component supported thereby |
US4817970A (en) * | 1986-05-23 | 1989-04-04 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Fluid seal having a divided ring disk |
US5456576A (en) * | 1994-08-31 | 1995-10-10 | United Technologies Corporation | Dynamic control of tip clearance |
FR2724412A1 (en) * | 1994-09-14 | 1996-03-15 | Snecma | TURBOMACHINE DAWN IN COMPOSITE MATERIAL WITH SEAL AND METHOD OF MAKING SAME |
EP1469165A1 (en) * | 2003-04-16 | 2004-10-20 | Snecma Moteurs | Reduction of the blade tip clearance in a gas turbine |
US20050175447A1 (en) * | 2004-02-09 | 2005-08-11 | Siemens Westinghouse Power Corporation | Compressor airfoils with movable tips |
EP1439281A3 (en) * | 2003-01-18 | 2006-10-18 | Rolls-Royce Deutschland Ltd & Co KG | Gas turbine engine blade |
US20070231128A1 (en) * | 2006-03-31 | 2007-10-04 | Caterpiller Inc. | Fan assembly |
US20090252602A1 (en) * | 2008-04-08 | 2009-10-08 | Siemens Power Generation, Inc. | Turbine blade tip gap reduction system |
US20090269189A1 (en) * | 2008-04-23 | 2009-10-29 | Rolls-Royce Plc | Fan blade |
US20110158793A1 (en) * | 2009-12-28 | 2011-06-30 | Fritsch Theodore J | Vane assembly having a vane end seal |
WO2013116500A1 (en) | 2012-01-31 | 2013-08-08 | United Technologies Corporation | Gas turbine rotary blade with tip insert |
US20140064937A1 (en) * | 2012-06-29 | 2014-03-06 | General Electric Company | Fan blade brush tip |
EP2980365A1 (en) * | 2014-07-30 | 2016-02-03 | MTU Aero Engines GmbH | Guide vane for a gas turbine with sealing elements on the face sides |
FR3025555A1 (en) * | 2014-09-09 | 2016-03-11 | Snecma | TURBINE DAWN AND TURBOMACHINE |
US10370995B2 (en) * | 2013-02-26 | 2019-08-06 | Rolls-Royce North American Technologies Inc. | Gas turbine engine vane end devices |
US11286036B2 (en) | 2018-10-12 | 2022-03-29 | Textron Innovations Inc. | Ducted rotor blade tip extension |
US11286037B2 (en) | 2018-10-12 | 2022-03-29 | Textron Innovations Inc. | Ducted rotor blade tip extension |
CN114576202A (en) * | 2022-02-28 | 2022-06-03 | 北京航空航天大学 | A kind of blade structure, compressor and compressor control method |
US11370536B2 (en) * | 2020-06-19 | 2022-06-28 | Textron Innovations Inc. | Tip gap control systems with active blade tips |
US11407504B2 (en) | 2020-06-19 | 2022-08-09 | Textron Innovations Inc. | Tip gap control systems with inner duct control surfaces |
US11479350B2 (en) | 2020-06-19 | 2022-10-25 | Textron Innovations Inc. | Tip gap monitoring systems for ducted aircraft |
US11565799B2 (en) | 2020-06-12 | 2023-01-31 | Textron Innovations Inc. | Adjustable ducted rotor blade tip extension |
FR3128741A1 (en) * | 2021-10-28 | 2023-05-05 | Safran Aircraft Engines | Device for varying a bypass ratio of a turbojet engine with variable length blades |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US625182A (en) * | 1899-05-16 | mason | ||
FR446821A (en) * | 1912-07-29 | 1912-12-16 | Neyret Brenier Et Cie Soc | Rotating joint for pumps and turbines |
DE389793C (en) * | 1922-02-15 | 1924-02-07 | Gustav De Grahl | Seal for screw pumps with decreasing pitch of the screw threads towards the pressure side |
US2776107A (en) * | 1955-03-11 | 1957-01-01 | Baldwin Lima Hamilton Corp | Hydraulic machine with adjustable propeller blades sealed at their inner ends |
US2814512A (en) * | 1952-06-03 | 1957-11-26 | Bristol Aeroplane Co Ltd | Sealing devices |
US2857150A (en) * | 1953-06-19 | 1958-10-21 | Shell Dev | Centrifugal pump for control systems and method of establishing a fluid pressure |
-
1963
- 1963-04-10 US US272141A patent/US3117716A/en not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US625182A (en) * | 1899-05-16 | mason | ||
FR446821A (en) * | 1912-07-29 | 1912-12-16 | Neyret Brenier Et Cie Soc | Rotating joint for pumps and turbines |
DE389793C (en) * | 1922-02-15 | 1924-02-07 | Gustav De Grahl | Seal for screw pumps with decreasing pitch of the screw threads towards the pressure side |
US2814512A (en) * | 1952-06-03 | 1957-11-26 | Bristol Aeroplane Co Ltd | Sealing devices |
US2857150A (en) * | 1953-06-19 | 1958-10-21 | Shell Dev | Centrifugal pump for control systems and method of establishing a fluid pressure |
US2776107A (en) * | 1955-03-11 | 1957-01-01 | Baldwin Lima Hamilton Corp | Hydraulic machine with adjustable propeller blades sealed at their inner ends |
Cited By (43)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3938906A (en) * | 1974-10-07 | 1976-02-17 | Westinghouse Electric Corporation | Slidable stator seal |
US4169692A (en) * | 1974-12-13 | 1979-10-02 | General Electric Company | Variable area turbine nozzle and means for sealing same |
US4193738A (en) * | 1977-09-19 | 1980-03-18 | General Electric Company | Floating seal for a variable area turbine nozzle |
FR2413418A1 (en) * | 1978-10-09 | 1979-07-27 | Diamond Shamrock Corp | PTFE-reinforced fluoro-polymer ion-exchange membrane - for cells producing chlorine and highly conc. alkali hydroxide |
US4411594A (en) * | 1979-06-30 | 1983-10-25 | Rolls-Royce Limited | Support member and a component supported thereby |
US4817970A (en) * | 1986-05-23 | 1989-04-04 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh | Fluid seal having a divided ring disk |
US5456576A (en) * | 1994-08-31 | 1995-10-10 | United Technologies Corporation | Dynamic control of tip clearance |
FR2724412A1 (en) * | 1994-09-14 | 1996-03-15 | Snecma | TURBOMACHINE DAWN IN COMPOSITE MATERIAL WITH SEAL AND METHOD OF MAKING SAME |
EP0708227A1 (en) * | 1994-09-14 | 1996-04-24 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Composite turbomachine blade with integrated brush seal and manufacturing method therefor |
US5628622A (en) * | 1994-09-14 | 1997-05-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Composite material turbine engine blade equipped with a seal and its production process |
EP1439281A3 (en) * | 2003-01-18 | 2006-10-18 | Rolls-Royce Deutschland Ltd & Co KG | Gas turbine engine blade |
EP1469165A1 (en) * | 2003-04-16 | 2004-10-20 | Snecma Moteurs | Reduction of the blade tip clearance in a gas turbine |
US20050008481A1 (en) * | 2003-04-16 | 2005-01-13 | Snecma Moteurs | Reducing clearance in a gas turbine |
US6976824B2 (en) | 2003-04-16 | 2005-12-20 | Snecma Moteurs | Reducing clearance in a gas turbine |
FR2853931A1 (en) * | 2003-04-16 | 2004-10-22 | Snecma Moteurs | REDUCING GAMES IN A GAS TURBINE |
US20050175447A1 (en) * | 2004-02-09 | 2005-08-11 | Siemens Westinghouse Power Corporation | Compressor airfoils with movable tips |
US6966755B2 (en) | 2004-02-09 | 2005-11-22 | Siemens Westinghouse Power Corporation | Compressor airfoils with movable tips |
US20070231128A1 (en) * | 2006-03-31 | 2007-10-04 | Caterpiller Inc. | Fan assembly |
US20090252602A1 (en) * | 2008-04-08 | 2009-10-08 | Siemens Power Generation, Inc. | Turbine blade tip gap reduction system |
US8262348B2 (en) | 2008-04-08 | 2012-09-11 | Siemens Energy, Inc. | Turbine blade tip gap reduction system |
EP2112330A3 (en) * | 2008-04-23 | 2017-11-08 | Rolls-Royce plc | Fan blade |
US20090269189A1 (en) * | 2008-04-23 | 2009-10-29 | Rolls-Royce Plc | Fan blade |
US8613596B2 (en) * | 2009-12-28 | 2013-12-24 | Rolls-Royce Corporation | Vane assembly having a vane end seal |
US20110158793A1 (en) * | 2009-12-28 | 2011-06-30 | Fritsch Theodore J | Vane assembly having a vane end seal |
WO2013116500A1 (en) | 2012-01-31 | 2013-08-08 | United Technologies Corporation | Gas turbine rotary blade with tip insert |
EP2809885A4 (en) * | 2012-01-31 | 2015-11-04 | United Technologies Corp | Gas turbine rotary blade with tip insert |
US9752441B2 (en) | 2012-01-31 | 2017-09-05 | United Technologies Corporation | Gas turbine rotary blade with tip insert |
US20140064937A1 (en) * | 2012-06-29 | 2014-03-06 | General Electric Company | Fan blade brush tip |
US11326464B2 (en) | 2013-02-26 | 2022-05-10 | Rolls-Royce North American Technologies Inc. | Gas turbine engine vane end devices |
US10370995B2 (en) * | 2013-02-26 | 2019-08-06 | Rolls-Royce North American Technologies Inc. | Gas turbine engine vane end devices |
US9932847B2 (en) | 2014-07-30 | 2018-04-03 | MTU Aero Engines AG | Guide blade for a gas turbine |
DE102014214914A1 (en) * | 2014-07-30 | 2016-03-03 | MTU Aero Engines AG | Guide vane for a gas turbine |
EP2980365A1 (en) * | 2014-07-30 | 2016-02-03 | MTU Aero Engines GmbH | Guide vane for a gas turbine with sealing elements on the face sides |
FR3025555A1 (en) * | 2014-09-09 | 2016-03-11 | Snecma | TURBINE DAWN AND TURBOMACHINE |
US11286036B2 (en) | 2018-10-12 | 2022-03-29 | Textron Innovations Inc. | Ducted rotor blade tip extension |
US11286037B2 (en) | 2018-10-12 | 2022-03-29 | Textron Innovations Inc. | Ducted rotor blade tip extension |
US11565799B2 (en) | 2020-06-12 | 2023-01-31 | Textron Innovations Inc. | Adjustable ducted rotor blade tip extension |
US11370536B2 (en) * | 2020-06-19 | 2022-06-28 | Textron Innovations Inc. | Tip gap control systems with active blade tips |
US11407504B2 (en) | 2020-06-19 | 2022-08-09 | Textron Innovations Inc. | Tip gap control systems with inner duct control surfaces |
US11479350B2 (en) | 2020-06-19 | 2022-10-25 | Textron Innovations Inc. | Tip gap monitoring systems for ducted aircraft |
FR3128741A1 (en) * | 2021-10-28 | 2023-05-05 | Safran Aircraft Engines | Device for varying a bypass ratio of a turbojet engine with variable length blades |
CN114576202A (en) * | 2022-02-28 | 2022-06-03 | 北京航空航天大学 | A kind of blade structure, compressor and compressor control method |
CN114576202B (en) * | 2022-02-28 | 2022-12-06 | 北京航空航天大学 | Blade structure, compressor and compressor control method |
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