US3689178A - Apparatus for protection of rotor vanes against surface erosion caused by impingement of high speed liquid drops - Google Patents

Apparatus for protection of rotor vanes against surface erosion caused by impingement of high speed liquid drops Download PDF

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US3689178A
US3689178A US91869A US3689178DA US3689178A US 3689178 A US3689178 A US 3689178A US 91869 A US91869 A US 91869A US 3689178D A US3689178D A US 3689178DA US 3689178 A US3689178 A US 3689178A
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baffles
vane
vanes
impingement
liquid drops
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US91869A
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Guy Faber
Carlo Maggi
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BBC Brown Boveri AG Germany
BBC Brown Boveri France SA
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BBC Brown Boveri France SA
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • ABSTRACT The surface of a structural part such as for example the leading edge portion of a turbine vane or airplane wing is protected against erosion which would otherwise be caused by impingement of high speed liquid drops thereon by positioning an array of flexible baffles in front of the surface. These baffles which areslightly spaced from the surface of the vane or wing serve to intercept the liquid drops resulting in a division thereof into smaller drops which are simultaneously decelerated as a result of flexation of the bafiles.
  • This invention relates to an improved device for the protection of the vanes of a rotor against erosion which are imperiled by liquid drops impinging thereon at high speed.
  • steam turbine vanes are produced either of an erosionproof 3O of stellite shields involves difiiculties in the case of titanium vanes because of the temperature influences during brazing, and in the case of plastic vanes because of the weight.
  • the properties of a material determinant for the erosion resistance namely strength combined with toughness, can hardly be increased any further, so that at increased circumferential speeds greater erosions are to be expected even with stellites.
  • the principal object underlying the present invention is to protect against the erosion of structural parts endangered by drop impact without having to subject the material to a special treatment and without having to replace it in the specially affected areas by a more erosion-resistant material.
  • a device for carrying out this method is characterized by baffle bodies of small mass which are arranged, viewed in the direction of incidence of the drops, ahead of the endangered structural parts.
  • baffle bodies which, due to their small mass, and because they do not rest on anything except for their attachment to the structural part to be protected, are flexible and hence can be elastically deflected in the direction of incidence or laterally thereto when a drop impinges.
  • This yielding of the baffle bodies upon impingement of a drop gives the same effect as a lower impingement speed. Due to the narrow and usually also curved impingement surface offered to the drops, the angle of incidence is more favorable than in the case of impingement normal to the impingement surface.
  • the drops are divided and so slowed in their velocity that the erosion effect on the imperiled structural parts behind the baffle bodies is greatly reduced.
  • thesestructural parts are, for example, the impellers of a low-pressure turbine, running in the saturated steam zone, they can be protected by preceding fixed baffle bodies installed in the flow path, e.g. a wire mesh.
  • the effect is greater if the baffle bodies co-rotate in the same direction of rotation as the vanes, preferably at the same speed. They may be fastened either to the rotor or to the vanes themselves. As the vanes are endangered by drop impact mainly toward the tip, it may sometimes be sufficient to protect only their radially external portion. The stress of the baffle bodies caused by the centrifugal force is thereby greatly reduced; yet it is advantageous to taper them conically in radial direction outwardly.
  • baffle bodies are fastened on the rotor or on the vanes, they are provided only in this region. Also it is not necessary to protect each vane separately, as five or six vanes are covered together and are sufficiently protected by baffle bodies mounted in front.
  • the baffle bodies may be made, for example, of colddrawnstainless steel. Experiments have shown that the erosion effect greatly decreases with decreasing wire diameter. A thickness of the baffle bodies of 1 mm is to be regarded practically as the upper limit. A few millimeters distance of the baffle bodies from the imperiled structural parts are sufficient for adequate protection.
  • FIG. 1 shows a steam turbine vane in front view
  • FIG. 2 a single baffle body on a larger scale
  • FIG. 3 an airplane wing in partial view.
  • the entrance edge of the turbine vane 1 is protected at its radially external portion by wires 2, which are secured to the ribs 3,4. They extend at a small distance from the vane approximately parallel with one another. Because of the high stress exerted by the centrifugal forces, a careful attachment to the ribs 3 is necessary.
  • FIG. 2 An example of this is illustrated in FIG. 2. It shows a single wire 2 greatly enlarged, especially the thickness being much exaggerated.
  • the outwardly tapering wire is welded into the rib 3, while at rib 4 it is fastened only by spot welding, because there only relatively small forces must be absorbed. According to the occurring stress, the wire may alternatively be jointed to the ribs by brazing or otherwise.
  • the profile may be recessed at this point, the wires extending in the original profile line, whereby the necessary spacing and the desired flexibility are established.
  • the wires may extend over the full length of the vane blade and may be held, for example, in a bottom plate, which is fastened to the root of the vane.
  • Another possibility already mentioned, consists in fastening the wires directly to the rotor, that is, in front of the vane root.
  • FIG. 3 shows another possible use of the baffle bodies. Before the nose of an airplane wing 5 a wire grid 6 is applied, which protects the planking against impinging rain drops.
  • baffle bodies are conceivable wherever high speeds occur, especially greater than Mach 1, and liquid drops are contained in the gaseous medium. Exchangeability of the baffle bodies is of advantage in most cases.
  • a device for protecting the vanes of a rotor against surface erosion caused by impingement of liquid drops thereon at high speed which comprises an array of thin flexible baffles positioned in front of and spaced from the surface of each vane, said baffles serving to intercept and decelerate the droplets prior to striking the vane surface as a result of flexation of said baffles, and said baffles also serving to divide the droplets into smaller masses, thereby to reduce their impact force upon the vane surface.
  • baffles are constituted by an array of parallel spaced thin flexible wires enveloping the leading edge portion of the vane and extending in a radially outward direction, said wires being spaced from the vane surface and being secured thereto only at their ends.
  • baffles are constituted by the wires of a thin flexible wire grid, said grid enveloping the leading edge portion of the vane and being secured thereto in spaced relation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The surface of a structural part such as for example the leading edge portion of a turbine vane or airplane wing is protected against erosion which would otherwise be caused by impingement of high speed liquid drops thereon by positioning an array of flexible baffles in front of the surface. These baffles which are slightly spaced from the surface of the vane or wing serve to intercept the liquid drops resulting in a division thereof into smaller drops which are simultaneously decelerated as a result of flexation of the baffles.

Description

United States Patent Faber et al.
[ Sept. 5, 1972 [54] APPARATUS FOR PROTECTION OF ROTOR VANES AGAINST SURFACE EROSION CAUSED BY IMPINGEMENT OF HIGH SPEED LIQUID DROPS [72] Inventors: Guy Faber, Oberrohrdorf; Carlo Maggi, Baden, both of Switzerland [73] Assignee: Aktiengesellschaft Brown, Boveri 8:
Cie, Baden, Switzerland 22 Filed: Nov. 23, 1970 [21] Appl.No.: 91,869
[30] Foreign Application Priority Data Dec. 23, 1969 Switzerland ..19070/69 [52] US. Cl ..416/224, 416/228 [51] 7 Int. Cl ..F01d 5/28 [58] Field of Search ..416/62, 224, 228; 415/ 168 [56] References Cited UNITED STATES PATENTS 1,862,827 6/ l 932 Parsons et a1 ..416/224 3,023,840 3/ 1962 Flamm ..416/224 X 3,347,520 10/ 1967 Onczarek ..416/228 X 3,365,126 1/19 68 StOfier et al ..416/228 3,403,893 l0/ 1968 Stoffer ..416/228 FOREIGN PATENTS OR APPLICATIONS 311,010 2/1919 Germany ..416/224 233,693 7/1969 U.S.S.R. ..416/224 Primary Examiner-Everette A. Powell, Jr. AttorneyPierce, Scheffler & Parker [57] ABSTRACT The surface of a structural part such as for example the leading edge portion of a turbine vane or airplane wing is protected against erosion which would otherwise be caused by impingement of high speed liquid drops thereon by positioning an array of flexible baffles in front of the surface. These baffles which areslightly spaced from the surface of the vane or wing serve to intercept the liquid drops resulting in a division thereof into smaller drops which are simultaneously decelerated as a result of flexation of the bafiles.
4 Claims, 3 Drawing Figures PATENTEDSEF 5 I912 3.6891 18 603 Faber Carlo M613 1;
3% law a fivkgglawmfww APPARATUS FOR PROTECTION OF ROTOR VANES AGAINST SURFACE EROSION CAUSED BY IMPINGEMENT OF HIGH SPEED LIQUID DROPS This invention relates to an improved device for the protection of the vanes of a rotor against erosion which are imperiled by liquid drops impinging thereon at high speed.
When liquid drops impinge on metals or other materials at very high speeds, they cause erosion, that is, small particles of material break off after a certain time. The erosion effect depends mainly on the speed of impingement of the drops, their diameter, the angle of incidence on the surface of the structural part, and the specific properties of the eroding material. Due to the removal, the surface first becomes rough, then peaks opposed to the impinging drops form, which are now removed more slowly but continue to be removed. The friction losses of a flow along such eroded surfaces are correspondingly great.
Low pressure vanes on steam turbines, running temporarily or permanently in the saturated steam zone, are very susceptible to erosion. Especially the radially external portion of the entrance edge may be eroded intensively, and this leads to a loss of efficiency. It should be taken into consideration also that eroded vanes can hardly be repaired.
For protection against erosion, therefore, steam turbine vanes are produced either of an erosionproof 3O of stellite shields involves difiiculties in the case of titanium vanes because of the temperature influences during brazing, and in the case of plastic vanes because of the weight. Also, in the case of stellites, the properties of a material determinant for the erosion resistance, namely strength combined with toughness, can hardly be increased any further, so that at increased circumferential speeds greater erosions are to be expected even with stellites.
When airplanes fly through rain clouds at supersonic speed, the wing noses are so intensively eroded by the rain drops that already after several times the planking consisting of a light metal alloy must be exchanged. The only remedy is seen in increasing the erosion resistance of the metals used.
The principal object underlying the present invention is to protect against the erosion of structural parts endangered by drop impact without having to subject the material to a special treatment and without having to replace it in the specially affected areas by a more erosion-resistant material.
This problem is solved according to the invention in that the drops are divided and, at the same time, decelerated before they impinge on the structural parts.
A device for carrying out this method is characterized by baffle bodies of small mass which are arranged, viewed in the direction of incidence of the drops, ahead of the endangered structural parts.
Instead of a fixed, stifi, solid erosion shield, there are used, according to the invention, baffle bodies which, due to their small mass, and because they do not rest on anything except for their attachment to the structural part to be protected, are flexible and hence can be elastically deflected in the direction of incidence or laterally thereto when a drop impinges. This yielding of the baffle bodies upon impingement of a drop gives the same effect as a lower impingement speed. Due to the narrow and usually also curved impingement surface offered to the drops, the angle of incidence is more favorable than in the case of impingement normal to the impingement surface. The drops are divided and so slowed in their velocity that the erosion effect on the imperiled structural parts behind the baffle bodies is greatly reduced. Y
If thesestructural parts are, for example, the impellers of a low-pressure turbine, running in the saturated steam zone, they can be protected by preceding fixed baffle bodies installed in the flow path, e.g. a wire mesh. However, the effect is greater if the baffle bodies co-rotate in the same direction of rotation as the vanes, preferably at the same speed. They may be fastened either to the rotor or to the vanes themselves. As the vanes are endangered by drop impact mainly toward the tip, it may sometimes be sufficient to protect only their radially external portion. The stress of the baffle bodies caused by the centrifugal force is thereby greatly reduced; yet it is advantageous to taper them conically in radial direction outwardly.
The drops impinge close to the stagnation or ram point of the profile, and therefore, if the baffle bodies are fastened on the rotor or on the vanes, they are provided only in this region. Also it is not necessary to protect each vane separately, as five or six vanes are covered together and are sufficiently protected by baffle bodies mounted in front.
The baffle bodies may be made, for example, of colddrawnstainless steel. Experiments have shown that the erosion effect greatly decreases with decreasing wire diameter. A thickness of the baffle bodies of 1 mm is to be regarded practically as the upper limit. A few millimeters distance of the baffle bodies from the imperiled structural parts are sufficient for adequate protection.
Two examples of construction of the invention are illustrated in simplified form in the accompanying drawings, wherein:
FIG. 1 shows a steam turbine vane in front view;
FIG. 2, a single baffle body on a larger scale; and
FIG. 3, an airplane wing in partial view.
According to FIG. 1, the entrance edge of the turbine vane 1 is protected at its radially external portion by wires 2, which are secured to the ribs 3,4. They extend at a small distance from the vane approximately parallel with one another. Because of the high stress exerted by the centrifugal forces, a careful attachment to the ribs 3 is necessary.
An example of this is illustrated in FIG. 2. It shows a single wire 2 greatly enlarged, especially the thickness being much exaggerated. The outwardly tapering wire is welded into the rib 3, while at rib 4 it is fastened only by spot welding, because there only relatively small forces must be absorbed. According to the occurring stress, the wire may alternatively be jointed to the ribs by brazing or otherwise.
Instead of providing the rib 3, the profile may be recessed at this point, the wires extending in the original profile line, whereby the necessary spacing and the desired flexibility are established. Also, the wires may extend over the full length of the vane blade and may be held, for example, in a bottom plate, which is fastened to the root of the vane. Another possibility, already mentioned, consists in fastening the wires directly to the rotor, that is, in front of the vane root.
FIG. 3 shows another possible use of the baffle bodies. Before the nose of an airplane wing 5 a wire grid 6 is applied, which protects the planking against impinging rain drops.
Other uses of the baffle bodies are conceivable wherever high speeds occur, especially greater than Mach 1, and liquid drops are contained in the gaseous medium. Exchangeability of the baffle bodies is of advantage in most cases.
We claim:
1. A device for protecting the vanes of a rotor against surface erosion caused by impingement of liquid drops thereon at high speed which comprises an array of thin flexible baffles positioned in front of and spaced from the surface of each vane, said baffles serving to intercept and decelerate the droplets prior to striking the vane surface as a result of flexation of said baffles, and said baffles also serving to divide the droplets into smaller masses, thereby to reduce their impact force upon the vane surface. I
v 2. A device as definedin claim 1 for protecting the vanes of a rotor against surface erosion wherein said baffles are constituted by an array of parallel spaced thin flexible wires enveloping the leading edge portion of the vane and extending in a radially outward direction, said wires being spaced from the vane surface and being secured thereto only at their ends.
3; A device as defined in claim 2 for protecting the vanes of a rotor against surface erosion wherein said wires are tapered in the radially outward direction.
4. A device as defined in claim 1 for protecting the vanesof a rotor-against surface erosion wherein said baffles are constituted by the wires of a thin flexible wire grid, said grid enveloping the leading edge portion of the vane and being secured thereto in spaced relation.
i t t i

Claims (4)

1. A device for protecting the vanes of a rotor against surface erosion caused by impingement of liquid drops thereon at high speed which comprises an array of thin flexible baffles positioned in front of and spaced from the surface of each vane, said baffles serving to intercept and decelerate the droplets prior to striking the vane surface as a result of flexation of said baffles, and said baffles also serving to divide the droplets into smaller masses, thereby to reduce their impact force upon the vane surface.
2. A device as defined in claim 1 for protecting the vanes of a rotor against surface erosion wherein said baffles are constituted by an array of parallel spaced thin flexible wires enveloping the leading edge portion of the vane and extending in a radially outward direction, said wires being spaced from the vane surface and being secured thereto only at their ends.
3. A device as defined in claim 2 for protecting the vanes of a rotor against surface erosion wherein said wires are tapered in the radially outward direction.
4. A device as defined in claim 1 for protecting the vanes of a rotor against surface erosion wherein said baffles are constituted by the wires of a thin flexible wire grid, said grid enveloping the leading edge portion of the vane and being secured thereto in spaced relation.
US91869A 1969-12-23 1970-11-23 Apparatus for protection of rotor vanes against surface erosion caused by impingement of high speed liquid drops Expired - Lifetime US3689178A (en)

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CH1907069A CH544216A (en) 1969-12-23 1969-12-23 Method and device for protecting components against drop impact

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6224339B1 (en) 1998-07-08 2001-05-01 Allison Advanced Development Company High temperature airfoil
US20050232757A1 (en) * 2003-05-27 2005-10-20 General Electric Company Wear resistant variable stator vane assemblies
US20060029494A1 (en) * 2003-05-27 2006-02-09 General Electric Company High temperature ceramic lubricant
US20060245676A1 (en) * 2005-04-28 2006-11-02 General Electric Company High temperature rod end bearings
WO2011002517A2 (en) * 2009-07-03 2011-01-06 Jon Kunowski Turbine powered personal flight system
ITMI20120779A1 (en) * 2012-05-08 2013-11-09 Franco Tosi Meccanica S P A ROTORIAL STAGE OF AXIAL TURBINE WITH AN IMPROVED EROSION PROTECTION
CN105604978A (en) * 2014-11-21 2016-05-25 中航商用航空发动机有限责任公司 Shock-resistant enhanced turbine engine fan blade
US20180135422A1 (en) * 2016-11-17 2018-05-17 United Technologies Corporation Airfoil with rods adjacent a core structure
US10670041B2 (en) * 2016-02-19 2020-06-02 Pratt & Whitney Canada Corp. Compressor rotor for supersonic flutter and/or resonant stress mitigation

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DE102008052380B4 (en) * 2008-10-20 2012-09-20 Siemens Aktiengesellschaft Turbine blade and turbine blade for a turbine and method for directly determining the erosion progress of a turbine blade
FR2972125B1 (en) * 2011-03-01 2013-04-12 Snecma METHOD FOR PRODUCING A METAL PIECE SUCH AS A TURBOMACHINE BLADE REINFORCEMENT

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SU233693A1 (en) * В. В. Крышев , Б. А. Ширков Центральный котлотурбинный институт И. И. Ползунова WORKING TURBO MOBILE
US1862827A (en) * 1930-01-22 1932-06-14 Parsons Steam turbine
US3023840A (en) * 1959-03-25 1962-03-06 Allis Chalmers Mfg Co Fluid displacing rotor device
US3347520A (en) * 1966-07-12 1967-10-17 Jerzy A Oweczarek Turbomachine blading
US3365126A (en) * 1965-09-01 1968-01-23 Gen Electric Compressor blade
US3403893A (en) * 1967-12-05 1968-10-01 Gen Electric Axial flow compressor blades

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DE311010C (en) *
SU233693A1 (en) * В. В. Крышев , Б. А. Ширков Центральный котлотурбинный институт И. И. Ползунова WORKING TURBO MOBILE
US1862827A (en) * 1930-01-22 1932-06-14 Parsons Steam turbine
US3023840A (en) * 1959-03-25 1962-03-06 Allis Chalmers Mfg Co Fluid displacing rotor device
US3365126A (en) * 1965-09-01 1968-01-23 Gen Electric Compressor blade
US3347520A (en) * 1966-07-12 1967-10-17 Jerzy A Oweczarek Turbomachine blading
US3403893A (en) * 1967-12-05 1968-10-01 Gen Electric Axial flow compressor blades

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6224339B1 (en) 1998-07-08 2001-05-01 Allison Advanced Development Company High temperature airfoil
US6322322B1 (en) 1998-07-08 2001-11-27 Allison Advanced Development Company High temperature airfoil
US20050232757A1 (en) * 2003-05-27 2005-10-20 General Electric Company Wear resistant variable stator vane assemblies
US20060029494A1 (en) * 2003-05-27 2006-02-09 General Electric Company High temperature ceramic lubricant
US7220098B2 (en) 2003-05-27 2007-05-22 General Electric Company Wear resistant variable stator vane assemblies
US20060245676A1 (en) * 2005-04-28 2006-11-02 General Electric Company High temperature rod end bearings
US7543992B2 (en) 2005-04-28 2009-06-09 General Electric Company High temperature rod end bearings
WO2011002517A3 (en) * 2009-07-03 2011-03-31 Jon Kunowski Turbine powered personal flight system
WO2011002517A2 (en) * 2009-07-03 2011-01-06 Jon Kunowski Turbine powered personal flight system
ITMI20120779A1 (en) * 2012-05-08 2013-11-09 Franco Tosi Meccanica S P A ROTORIAL STAGE OF AXIAL TURBINE WITH AN IMPROVED EROSION PROTECTION
CN105604978A (en) * 2014-11-21 2016-05-25 中航商用航空发动机有限责任公司 Shock-resistant enhanced turbine engine fan blade
CN105604978B (en) * 2014-11-21 2018-03-23 中国航发商用航空发动机有限责任公司 The enhanced turbogenerator fan blade of shock resistance
US10670041B2 (en) * 2016-02-19 2020-06-02 Pratt & Whitney Canada Corp. Compressor rotor for supersonic flutter and/or resonant stress mitigation
US11353038B2 (en) 2016-02-19 2022-06-07 Pratt & Whitney Canada Corp. Compressor rotor for supersonic flutter and/or resonant stress mitigation
US20180135422A1 (en) * 2016-11-17 2018-05-17 United Technologies Corporation Airfoil with rods adjacent a core structure
US10598025B2 (en) * 2016-11-17 2020-03-24 United Technologies Corporation Airfoil with rods adjacent a core structure

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DE2014290A1 (en) 1971-07-01
FR2074077A5 (en) 1971-10-01
CH544216A (en) 1973-11-15

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