US2431660A - Turbine blade - Google Patents
Turbine blade Download PDFInfo
- Publication number
- US2431660A US2431660A US633196A US63319645A US2431660A US 2431660 A US2431660 A US 2431660A US 633196 A US633196 A US 633196A US 63319645 A US63319645 A US 63319645A US 2431660 A US2431660 A US 2431660A
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- Prior art keywords
- blade
- metal
- set forth
- ceramic
- turbine blade
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- Expired - Lifetime
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- 239000000843 powder Substances 0.000 description 31
- 229910052751 metal Inorganic materials 0.000 description 24
- 239000002184 metal Substances 0.000 description 24
- 239000000919 ceramic Substances 0.000 description 17
- 229910000831 Steel Inorganic materials 0.000 description 11
- 239000010959 steel Substances 0.000 description 11
- 239000000203 mixture Substances 0.000 description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 6
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 6
- 239000011521 glass Substances 0.000 description 5
- 239000012530 fluid Substances 0.000 description 4
- 239000007789 gas Substances 0.000 description 3
- 229910052742 iron Inorganic materials 0.000 description 3
- 239000010410 layer Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000008018 melting Effects 0.000 description 3
- 238000002844 melting Methods 0.000 description 3
- 229910052759 nickel Inorganic materials 0.000 description 3
- FRWYFWZENXDZMU-UHFFFAOYSA-N 2-iodoquinoline Chemical compound C1=CC=CC2=NC(I)=CC=C21 FRWYFWZENXDZMU-UHFFFAOYSA-N 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- LTPBRCUWZOMYOC-UHFFFAOYSA-N beryllium oxide Inorganic materials O=[Be] LTPBRCUWZOMYOC-UHFFFAOYSA-N 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 239000011651 chromium Substances 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 229910052750 molybdenum Inorganic materials 0.000 description 2
- 239000011733 molybdenum Substances 0.000 description 2
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 description 2
- 229910052573 porcelain Inorganic materials 0.000 description 2
- 239000010453 quartz Substances 0.000 description 2
- 239000003870 refractory metal Substances 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- ZSLUVFAKFWKJRC-IGMARMGPSA-N 232Th Chemical compound [232Th] ZSLUVFAKFWKJRC-IGMARMGPSA-N 0.000 description 1
- XMTQQYYKAHVGBJ-UHFFFAOYSA-N 3-(3,4-DICHLOROPHENYL)-1,1-DIMETHYLUREA Chemical compound CN(C)C(=O)NC1=CC=C(Cl)C(Cl)=C1 XMTQQYYKAHVGBJ-UHFFFAOYSA-N 0.000 description 1
- RZVAJINKPMORJF-UHFFFAOYSA-N Acetaminophen Chemical compound CC(=O)NC1=CC=C(O)C=C1 RZVAJINKPMORJF-UHFFFAOYSA-N 0.000 description 1
- 239000005995 Aluminium silicate Substances 0.000 description 1
- 229910000952 Be alloy Inorganic materials 0.000 description 1
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 229910052776 Thorium Inorganic materials 0.000 description 1
- GWEVSGVZZGPLCZ-UHFFFAOYSA-N Titan oxide Chemical compound O=[Ti]=O GWEVSGVZZGPLCZ-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 235000012211 aluminium silicate Nutrition 0.000 description 1
- 229910052790 beryllium Inorganic materials 0.000 description 1
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 239000005293 duran Substances 0.000 description 1
- 239000010433 feldspar Substances 0.000 description 1
- 239000003779 heat-resistant material Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- NLYAJNPCOHFWQQ-UHFFFAOYSA-N kaolin Chemical compound O.O.O=[Al]O[Si](=O)O[Si](=O)O[Al]=O NLYAJNPCOHFWQQ-UHFFFAOYSA-N 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000011241 protective layer Substances 0.000 description 1
- 239000005297 pyrex Substances 0.000 description 1
- 239000002893 slag Substances 0.000 description 1
- 229910052596 spinel Inorganic materials 0.000 description 1
- 239000011029 spinel Substances 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- 239000000454 talc Substances 0.000 description 1
- 229910052623 talc Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- OGIDPMRJRNCKJF-UHFFFAOYSA-N titanium oxide Inorganic materials [Ti]=O OGIDPMRJRNCKJF-UHFFFAOYSA-N 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- UONOETXJSWQNOL-UHFFFAOYSA-N tungsten carbide Chemical compound [W+]#[C-] UONOETXJSWQNOL-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
- 229910052726 zirconium Inorganic materials 0.000 description 1
- GFQYVLUOOAAOGM-UHFFFAOYSA-N zirconium(iv) silicate Chemical compound [Zr+4].[O-][Si]([O-])([O-])[O-] GFQYVLUOOAAOGM-UHFFFAOYSA-N 0.000 description 1
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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- 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
- Y10S264/00—Plastic and nonmetallic article shaping or treating: processes
- Y10S264/36—Processes of making metal-ceramics
-
- 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
- Y10S60/00—Power plants
- Y10S60/909—Reaction motor or component composed of specific material
-
- 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
- Y10T29/49337—Composite blade
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12014—All metal or with adjacent metals having metal particles
- Y10T428/12021—All metal or with adjacent metals having metal particles having composition or density gradient or differential porosity
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12014—All metal or with adjacent metals having metal particles
- Y10T428/12028—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, etc.]
- Y10T428/12063—Nonparticulate metal component
- Y10T428/12139—Nonmetal particles in particulate component
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]
Definitions
- This invention relates generally to the construction of turbine blades or vanes and it has particular relation to blades for turbines which operate at extremely high temperatures.
- a turbine blade for use with high temperature power-generating fluids should have the following properties: high tensile strength in the temperature range above 700 0., low specific weight, high heat conductivity and capability of enduring temperature changes, relatively great surface hardness, capability of simple and durable installation, and resistance to oxidation, 1, e. relatively free from slag formation.
- the blade or vane has a metal foot or root portion to which is joined a top or working portion on which the high temperature fluid impinges and which is formed of, or provided with a covering or layer of, fritted metal and ceramic powder or ceramic-like powder, the metal content of the working portion decreasing with increasing distance from the foot portion of the blade.
- a turbine blade thus stratified and having a steel foot portion can be installed on a turbine rotor in exactly the same manner and as easily as one made wholly of steel.
- the steel foot portion may gradually merge into the interior of the composite top or working portion of the blade.
- Figures 1 and 2 are side elevations, partly in section, of two different embodiments of the present invention.
- the foot or root portion a of the blade is formed of a suitable steel and shaped to conform to the design of the stator and rotor mountings of the turbine, for example a de Laval turbine, in which it is to be incorporated.
- the root portion a is tapered outwardly and located within the working portion b which pin e upon the turbine blade.
- .metal powder may be of a corrosion-resistant steel that is not damaged by the high temperature gases that drive the turbine.
- the root section a need not extend into the interior of the blade section but may be welded to the inner end of the working portion b of the turbine blade, As in the turbine blade of Fig. l, the composition of the fritted blade portion b changes gradually from a substantial all-metal section adjacent the steel root a to a substantially all-ceramic section or layer at the outer surface of the blade.
- the metal powders of the fritted portion may be of a single metal or mixtures of metals such as iron, nickel, chromium, cobalt, tungsten, molybdenum or titanium; may be a steel including some of the recited refractory metals; or may be alloys of refractory metals, particularly steels or alloys of high tensile strength; metal powders of hard metal alloys such as tungsten carbide, either is composed of a fritted mixture of metal powder and ceramic or ceramic-like powder. The ratio of metal powder to ceramic powder decreases progressively with increasing distance from the steel root portion a of the blade.
- the metal powder content adjacent the steel root portion a is so high as to result in a welding of the fritted working portion b to the root portion a.
- the outer end of the working portion b of the blade, or at least the surface layer of the blade, is a fritted mass of ceramic or ceramic-like powder with little or no admixed metal powder.
- the outer fritted layer of ceramic or ceramic-like material is sufilciently compact to be substantially impermeable to the high temperature gases that imwith or without additions of cobalt and/or nickel powders are also suitable.
- the ceramic powder is selected from the refractory oxides of highly heat resistant materials and preferably from relatively stable oxides having relatively high heat conductivity; for example oxides of beryllium, aluminum, zirconium, magnesium and thorium. Mixtures of oxides are also suitable, such as spinel, zirconium silicate and others together with oxides having lower melting points such as quartz and titanium oxide; also porcelain comprising a mixture of kaolin, quartz and feldspar or the steatite group with talc or soapstone as the main component. Powdered glass may be used alone or in combination with the refractory oxides, the glass being of a hard or high temperature type such as the so-called oven glasses sold under the trade-marks Pyrex and Duran.
- the weight of the fritted blade portion is substantially less than that of an all-metal blade, and the stresses due to centrifugal force are therefore substantially reduced.
- Ceramic materials such as beryllium oxide or aluminum oxide are particularly useful as they have a heat conductivity similar to that of iron and steel. These oxides have meltin points above 2000 C. and, when vitrified, have a surface hardness greater than that of hardened steels.
- a turbine blade or vane for use with high temperature pressure fluids said blade comprising a metal foot portion for attachment to a rotor or stator ring, and a working portion carried by and extending from said foot portion, the
- the metal powder consists at least in part of working portion of the blade that is impinged upon by said fluids being a fritted mixture of metal and ceramic powders, the metal content of the blade decreasing as the distance from the foot portion increases.
- the ceramic powder comprises oxides of highly fire-proof materials having high melting points.
- the ceramic powder comprises oxides of highly fire-proof materials having high melting points and high heat conductivity.
- the metal powder comprises an alloy of high .tensile strength.
- the metal powder comprises hard metal alloys of high tensile strength.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Nov. 25, 194.7. A. GAUDENZI TURBINE BLADE Filed Dec. 6, 1945 2 -Wu m a Patented Nov. 25, 1947 TURBINE BLADE Arthur Gaudenzi, Wettingen, Switzerland, as-
signor to Aktiengesellschaft Brown, Boveri & Ole, Baden, Switzerland, a joint-stock company Application December 6, 1945, Serial No. 633,196 In Switzerland December 1, 1944 Section 1, Public Law 690, August 8, 1946 19 Claims.
This invention relates generally to the construction of turbine blades or vanes and it has particular relation to blades for turbines which operate at extremely high temperatures.
A turbine blade for use with high temperature power-generating fluids, such as gas turbine blades, should have the following properties: high tensile strength in the temperature range above 700 0., low specific weight, high heat conductivity and capability of enduring temperature changes, relatively great surface hardness, capability of simple and durable installation, and resistance to oxidation, 1, e. relatively free from slag formation.
In accordance with this invention the blade or vane has a metal foot or root portion to which is joined a top or working portion on which the high temperature fluid impinges and which is formed of, or provided with a covering or layer of, fritted metal and ceramic powder or ceramic-like powder, the metal content of the working portion decreasing with increasing distance from the foot portion of the blade. A turbine blade thus stratified and having a steel foot portion can be installed on a turbine rotor in exactly the same manner and as easily as one made wholly of steel. The steel foot portion may gradually merge into the interior of the composite top or working portion of the blade.
In the drawing, Figures 1 and 2 are side elevations, partly in section, of two different embodiments of the present invention.
In both of the illustrated embodiments of the invention, the foot or root portion a of the blade is formed of a suitable steel and shaped to conform to the design of the stator and rotor mountings of the turbine, for example a de Laval turbine, in which it is to be incorporated. As shown in Fig. 1, the root portion a is tapered outwardly and located within the working portion b which pin e upon the turbine blade. Alternatively, the
.metal powder may be of a corrosion-resistant steel that is not damaged by the high temperature gases that drive the turbine.
As shown in Fig. 2. the root section a need not extend into the interior of the blade section but may be welded to the inner end of the working portion b of the turbine blade, As in the turbine blade of Fig. l, the composition of the fritted blade portion b changes gradually from a substantial all-metal section adjacent the steel root a to a substantially all-ceramic section or layer at the outer surface of the blade.
The metal powders of the fritted portion may be of a single metal or mixtures of metals such as iron, nickel, chromium, cobalt, tungsten, molybdenum or titanium; may be a steel including some of the recited refractory metals; or may be alloys of refractory metals, particularly steels or alloys of high tensile strength; metal powders of hard metal alloys such as tungsten carbide, either is composed of a fritted mixture of metal powder and ceramic or ceramic-like powder. The ratio of metal powder to ceramic powder decreases progressively with increasing distance from the steel root portion a of the blade. The metal powder content adjacent the steel root portion a is so high as to result in a welding of the fritted working portion b to the root portion a. The outer end of the working portion b of the blade, or at least the surface layer of the blade, is a fritted mass of ceramic or ceramic-like powder with little or no admixed metal powder. The outer fritted layer of ceramic or ceramic-like material is sufilciently compact to be substantially impermeable to the high temperature gases that imwith or without additions of cobalt and/or nickel powders are also suitable.
The ceramic powder is selected from the refractory oxides of highly heat resistant materials and preferably from relatively stable oxides having relatively high heat conductivity; for example oxides of beryllium, aluminum, zirconium, magnesium and thorium. Mixtures of oxides are also suitable, such as spinel, zirconium silicate and others together with oxides having lower melting points such as quartz and titanium oxide; also porcelain comprising a mixture of kaolin, quartz and feldspar or the steatite group with talc or soapstone as the main component. Powdered glass may be used alone or in combination with the refractory oxides, the glass being of a hard or high temperature type such as the so-called oven glasses sold under the trade-marks Pyrex and Duran.
The weight of the fritted blade portion is substantially less than that of an all-metal blade, and the stresses due to centrifugal force are therefore substantially reduced. Ceramic materials such as beryllium oxide or aluminum oxide are particularly useful as they have a heat conductivity similar to that of iron and steel. These oxides have meltin points above 2000 C. and, when vitrified, have a surface hardness greater than that of hardened steels.
I claim:
1. A turbine blade or vane for use with high temperature pressure fluids said blade comprising a metal foot portion for attachment to a rotor or stator ring, and a working portion carried by and extending from said foot portion, the
in the metal powder consists at least in part of working portion of the blade that is impinged upon by said fluids being a fritted mixture of metal and ceramic powders, the metal content of the blade decreasing as the distance from the foot portion increases.
2. The invention as set forth in claim 1, wherein the ceramic powder comprises oxides of highly fire-proof materials having high melting points.
3. The invention as set forth in claim 1, wherein the ceramic powder comprises oxides of highly fire-proof materials having high melting points and high heat conductivity. I
4. The invention as set forth in claim 1, wherein the ceramic powder consists at-least in part of beryllium oxide.
5. The invention as set forth in claim 1, wherein the ceramic powder consists at least in part of aluminum oxide.
6. The invention as set forth in claim 1, wherein the ceramic powder comprises a mixture of oxides.
7. The invention as set forth in claim 1, wherein the ceramic powder consists at least in part of porcelain.
8. The invention as set forth in claim 1, wherein the ceramic powder consists at least in part of steatites.
9. The invention as set forth in claim 1, wherein the ceramic powder consists at least in part of glass powder from hard glasses.
10. The invention as set forth in claim 1, wherein the metal powder consists at least in part of iron.
11. The invention as set forth in claim 1, wherein the metal powder consists at least in part of nickel.
12. The invention as set forth in claim 1, wherein the metal powder consists at least in part of chromium.
Y 4 1s. The invention as set forth in claim 1, where.-
molybdenum.
14. The invention as set forth in claim 1, wherein the metal powder comprises an alloy of high .tensile strength.
15. The invention as set forth in claim 1, wherein the metal powder comprises hard metal alloys of high tensile strength.
16. The invention'as set forth in claim 1, wherein the foot portion protrudes into the working portion and merges into the same in the interior thereof.
- 17. The invention. as set forth in claim'i, wherein the working portion is provided with a protective layer offritted metal and ceramic powder on all sides.
18. The invention, as set forth in claim 1, wherein the foot portion protrudes into the working portion and merges into the same in the in- REFERENCES CITED The following references are of record in the file of this patent:
FOREIGN PATENTS Country Date Italy 1940 OTHER REFERENCES Ser. No. 385,333, Schutte (A. P. C.) pub. May
Number
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH2431660X | 1944-12-01 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2431660A true US2431660A (en) | 1947-11-25 |
Family
ID=4569213
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US633196A Expired - Lifetime US2431660A (en) | 1944-12-01 | 1945-12-06 | Turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US2431660A (en) |
Cited By (58)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2653377A (en) * | 1947-09-02 | 1953-09-29 | American Electro Metal Corp | Method for forming metal powder into a fluid guiding body |
| US2656596A (en) * | 1949-05-17 | 1953-10-27 | Union Carbide & Carbon Corp | Tungsten-chromium-alumina metal ceramics |
| US2694646A (en) * | 1949-07-19 | 1954-11-16 | Zirconium Corp Of America | Zirconia compositions |
| US2694851A (en) * | 1948-04-28 | 1954-11-23 | Daniel A Marra | Method of forming torch tips |
| US2696652A (en) * | 1951-07-25 | 1954-12-14 | Raytheon Mfg Co | Quartz article and method for fabricating it |
| US2698990A (en) * | 1950-01-25 | 1955-01-11 | Union Carbide & Carbon Corp | Chromium-alumina metal ceramics |
| US2715011A (en) * | 1949-07-19 | 1955-08-09 | Maschf Augsburg Nuernberg Ag | Ceramic blade for turbine engine |
| US2749029A (en) * | 1948-11-26 | 1956-06-05 | Sintercast Corp America | Compressor blade |
| US2751188A (en) * | 1950-02-25 | 1956-06-19 | Maschf Augsburg Nuernberg Ag | Ceramic product |
| US2751293A (en) * | 1951-07-31 | 1956-06-19 | Allied Prod Corp | Process of making perforated powdered metal article |
| US2753612A (en) * | 1956-07-10 | Process of forming magnesia refractory | ||
| US2767463A (en) * | 1951-04-19 | 1956-10-23 | Onera (Off Nat Aerospatiale) | Metallo-ceramic compositions and process of producing same |
| US2769611A (en) * | 1951-08-15 | 1956-11-06 | Schwarzkopf Dev Co | Gas turbine rotors and their production |
| US2775426A (en) * | 1951-12-20 | 1956-12-25 | Westinghouse Electric Corp | Blade structure |
| US2783967A (en) * | 1952-01-03 | 1957-03-05 | Maschf Augsburg Nuernberg Ag | Ceramic machine parts |
| US2783966A (en) * | 1948-10-22 | 1957-03-05 | Maschf Augsburg Nuernberg Ag | Parts for machinery |
| US2819515A (en) * | 1951-06-26 | 1958-01-14 | Thompson Prod Inc | Method of making a blade |
| US2826512A (en) * | 1953-08-14 | 1958-03-11 | Jack F Govan | Method of coating and resulting product |
| US2829427A (en) * | 1948-10-13 | 1958-04-08 | Onera (Off Nat Aerospatiale) | Sintered refractory material |
| US2859163A (en) * | 1957-12-30 | 1958-11-04 | George L Ploetz | Cadmium-rare earth borate glass as reactor control material |
| US2872726A (en) * | 1955-01-04 | 1959-02-10 | Gen Electric | Sintered hard compositions |
| US2872724A (en) * | 1953-07-31 | 1959-02-10 | Union Carbide Corp | Oxidized chromium-alumina metal ceramic protective tube |
| US2909834A (en) * | 1955-10-14 | 1959-10-27 | Union Carbide Corp | Cermets with high impact strength |
| US2920830A (en) * | 1956-12-26 | 1960-01-12 | Niro Atomizer As | Atomizer for the atomization of liquid dispersions in a reaction chamber |
| US2941281A (en) * | 1953-12-04 | 1960-06-21 | Int Nickel Co | Hot workable, heat resistant metal bodies |
| US2954208A (en) * | 1953-01-09 | 1960-09-27 | Gen Motors Corp | Air foil section |
| US2957238A (en) * | 1953-11-18 | 1960-10-25 | Rca Corp | Method of forming a metallic surface layer on a ferrospinel body and bonding the same |
| US2961325A (en) * | 1957-06-21 | 1960-11-22 | American Lava Corp | Cermet bodies |
| US2994124A (en) * | 1955-10-03 | 1961-08-01 | Gen Electric | Clad cermet body |
| US3011761A (en) * | 1954-11-25 | 1961-12-05 | Power Jets Res & Dev Ltd | Turbine blades |
| US3030071A (en) * | 1959-09-22 | 1962-04-17 | Gen Electric | Erosion-resistant turbine blade |
| US3032316A (en) * | 1958-10-09 | 1962-05-01 | Bruce E Kramer | Jet turbine buckets and method of making the same |
| US3047938A (en) * | 1958-03-31 | 1962-08-07 | Gen Motors Corp | High temperature bond and method of forming same |
| US3052016A (en) * | 1958-03-19 | 1962-09-04 | Ind Fernand Courtoy Bureau Et | Structure for joining by fusion-welding of ferritic steel with austenitic steel |
| US3066391A (en) * | 1957-01-15 | 1962-12-04 | Crucible Steel Co America | Powder metallurgy processes and products |
| US3123447A (en) * | 1964-03-03 | Zirconium to stainless steel connection | ||
| US3123470A (en) * | 1964-03-03 | Bonding means and method | ||
| US3148981A (en) * | 1961-04-21 | 1964-09-15 | Nat Beryllia Corp | Metal-oxide gradient ceramic bodies |
| US3175279A (en) * | 1962-03-23 | 1965-03-30 | Bendix Corp | Ductile chromium composition |
| US3181947A (en) * | 1957-01-15 | 1965-05-04 | Crucible Steel Co America | Powder metallurgy processes and products |
| US3188961A (en) * | 1961-05-25 | 1965-06-15 | Bendix Corp | Means for cooling structures that are periodically heated to elevated temperatures |
| US3215511A (en) * | 1962-03-30 | 1965-11-02 | Union Carbide Corp | Gas turbine nozzle vane and like articles |
| US3284194A (en) * | 1962-03-23 | 1966-11-08 | Bendix Corp | Method of forming ductile metals |
| US3294496A (en) * | 1963-11-29 | 1966-12-27 | Union Carbide Corp | Metal ceramic compositions |
| US3320036A (en) * | 1964-10-26 | 1967-05-16 | Bendix Corp | Ductile molybdenum composition containing a spinel dispersion |
| US3320037A (en) * | 1964-10-26 | 1967-05-16 | Bendix Corp | Ductile tungsten composition containing a spinel dispersed uniformly throughout |
| DE1751813B1 (en) * | 1968-07-26 | 1971-04-29 | Sulzer Ag | GUIDE VANE FOR FLOW MACHINE |
| US3982854A (en) * | 1971-12-20 | 1976-09-28 | General Electric Company | Friction welded metallic turbomachinery blade element |
| US4063939A (en) * | 1975-06-27 | 1977-12-20 | Special Metals Corporation | Composite turbine wheel and process for making same |
| US4362471A (en) * | 1974-11-29 | 1982-12-07 | Volkswagenwerk Aktiengesellschaft | Article, such as a turbine rotor and blade which comprises a first zone of a nonoxide ceramic material and a second zone of a softer material |
| US4512719A (en) * | 1981-07-24 | 1985-04-23 | Motoren-Un Turbinen-Union Munchen Gmbh | Hot gas wetted turbine blade |
| EP0139396A1 (en) * | 1983-08-29 | 1985-05-02 | Westinghouse Electric Corporation | Combustion turbine blade with varying coating |
| US4597926A (en) * | 1981-11-30 | 1986-07-01 | Tokyo Shibaura Denki Kabushiki Kaisha | Method of manufacturing radial flow turbine rotor |
| DE4219470A1 (en) * | 1992-06-13 | 1993-12-16 | Asea Brown Boveri | Component for high temperatures, in particular turbine blade, and method for producing this component |
| EP0574727A1 (en) * | 1992-06-13 | 1993-12-22 | Asea Brown Boveri Ag | Method for the production of a high temperature-resistant element from two different materials |
| US5476723A (en) * | 1992-05-27 | 1995-12-19 | Societe Nationale D'etude Et De Construction De Motors D'aviation "S.N.E.C.M.A." | Coated superalloy component |
| US20060204769A1 (en) * | 2002-12-18 | 2006-09-14 | Alessandro Coppola | Manufacturing method for obtaining high-performance components for gas turbines and components thus obtained |
| US11261742B2 (en) | 2013-11-19 | 2022-03-01 | Raytheon Technologies Corporation | Article having variable composition coating |
-
1945
- 1945-12-06 US US633196A patent/US2431660A/en not_active Expired - Lifetime
Cited By (60)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3123447A (en) * | 1964-03-03 | Zirconium to stainless steel connection | ||
| US3123470A (en) * | 1964-03-03 | Bonding means and method | ||
| US2753612A (en) * | 1956-07-10 | Process of forming magnesia refractory | ||
| US2653377A (en) * | 1947-09-02 | 1953-09-29 | American Electro Metal Corp | Method for forming metal powder into a fluid guiding body |
| US2694851A (en) * | 1948-04-28 | 1954-11-23 | Daniel A Marra | Method of forming torch tips |
| US2829427A (en) * | 1948-10-13 | 1958-04-08 | Onera (Off Nat Aerospatiale) | Sintered refractory material |
| US2783966A (en) * | 1948-10-22 | 1957-03-05 | Maschf Augsburg Nuernberg Ag | Parts for machinery |
| US2749029A (en) * | 1948-11-26 | 1956-06-05 | Sintercast Corp America | Compressor blade |
| US2656596A (en) * | 1949-05-17 | 1953-10-27 | Union Carbide & Carbon Corp | Tungsten-chromium-alumina metal ceramics |
| US2694646A (en) * | 1949-07-19 | 1954-11-16 | Zirconium Corp Of America | Zirconia compositions |
| US2715011A (en) * | 1949-07-19 | 1955-08-09 | Maschf Augsburg Nuernberg Ag | Ceramic blade for turbine engine |
| US2698990A (en) * | 1950-01-25 | 1955-01-11 | Union Carbide & Carbon Corp | Chromium-alumina metal ceramics |
| US2751188A (en) * | 1950-02-25 | 1956-06-19 | Maschf Augsburg Nuernberg Ag | Ceramic product |
| US2767463A (en) * | 1951-04-19 | 1956-10-23 | Onera (Off Nat Aerospatiale) | Metallo-ceramic compositions and process of producing same |
| US2819515A (en) * | 1951-06-26 | 1958-01-14 | Thompson Prod Inc | Method of making a blade |
| US2696652A (en) * | 1951-07-25 | 1954-12-14 | Raytheon Mfg Co | Quartz article and method for fabricating it |
| US2751293A (en) * | 1951-07-31 | 1956-06-19 | Allied Prod Corp | Process of making perforated powdered metal article |
| US2769611A (en) * | 1951-08-15 | 1956-11-06 | Schwarzkopf Dev Co | Gas turbine rotors and their production |
| US2775426A (en) * | 1951-12-20 | 1956-12-25 | Westinghouse Electric Corp | Blade structure |
| US2783967A (en) * | 1952-01-03 | 1957-03-05 | Maschf Augsburg Nuernberg Ag | Ceramic machine parts |
| US2954208A (en) * | 1953-01-09 | 1960-09-27 | Gen Motors Corp | Air foil section |
| US2872724A (en) * | 1953-07-31 | 1959-02-10 | Union Carbide Corp | Oxidized chromium-alumina metal ceramic protective tube |
| US2826512A (en) * | 1953-08-14 | 1958-03-11 | Jack F Govan | Method of coating and resulting product |
| US2957238A (en) * | 1953-11-18 | 1960-10-25 | Rca Corp | Method of forming a metallic surface layer on a ferrospinel body and bonding the same |
| US2941281A (en) * | 1953-12-04 | 1960-06-21 | Int Nickel Co | Hot workable, heat resistant metal bodies |
| US3011761A (en) * | 1954-11-25 | 1961-12-05 | Power Jets Res & Dev Ltd | Turbine blades |
| US2872726A (en) * | 1955-01-04 | 1959-02-10 | Gen Electric | Sintered hard compositions |
| US2994124A (en) * | 1955-10-03 | 1961-08-01 | Gen Electric | Clad cermet body |
| US2909834A (en) * | 1955-10-14 | 1959-10-27 | Union Carbide Corp | Cermets with high impact strength |
| US2920830A (en) * | 1956-12-26 | 1960-01-12 | Niro Atomizer As | Atomizer for the atomization of liquid dispersions in a reaction chamber |
| US3181947A (en) * | 1957-01-15 | 1965-05-04 | Crucible Steel Co America | Powder metallurgy processes and products |
| US3066391A (en) * | 1957-01-15 | 1962-12-04 | Crucible Steel Co America | Powder metallurgy processes and products |
| US2961325A (en) * | 1957-06-21 | 1960-11-22 | American Lava Corp | Cermet bodies |
| US2859163A (en) * | 1957-12-30 | 1958-11-04 | George L Ploetz | Cadmium-rare earth borate glass as reactor control material |
| US3052016A (en) * | 1958-03-19 | 1962-09-04 | Ind Fernand Courtoy Bureau Et | Structure for joining by fusion-welding of ferritic steel with austenitic steel |
| US3047938A (en) * | 1958-03-31 | 1962-08-07 | Gen Motors Corp | High temperature bond and method of forming same |
| US3032316A (en) * | 1958-10-09 | 1962-05-01 | Bruce E Kramer | Jet turbine buckets and method of making the same |
| US3030071A (en) * | 1959-09-22 | 1962-04-17 | Gen Electric | Erosion-resistant turbine blade |
| US3148981A (en) * | 1961-04-21 | 1964-09-15 | Nat Beryllia Corp | Metal-oxide gradient ceramic bodies |
| US3188961A (en) * | 1961-05-25 | 1965-06-15 | Bendix Corp | Means for cooling structures that are periodically heated to elevated temperatures |
| US3175279A (en) * | 1962-03-23 | 1965-03-30 | Bendix Corp | Ductile chromium composition |
| US3284194A (en) * | 1962-03-23 | 1966-11-08 | Bendix Corp | Method of forming ductile metals |
| US3215511A (en) * | 1962-03-30 | 1965-11-02 | Union Carbide Corp | Gas turbine nozzle vane and like articles |
| US3294496A (en) * | 1963-11-29 | 1966-12-27 | Union Carbide Corp | Metal ceramic compositions |
| US3320036A (en) * | 1964-10-26 | 1967-05-16 | Bendix Corp | Ductile molybdenum composition containing a spinel dispersion |
| US3320037A (en) * | 1964-10-26 | 1967-05-16 | Bendix Corp | Ductile tungsten composition containing a spinel dispersed uniformly throughout |
| DE1751813B1 (en) * | 1968-07-26 | 1971-04-29 | Sulzer Ag | GUIDE VANE FOR FLOW MACHINE |
| US3982854A (en) * | 1971-12-20 | 1976-09-28 | General Electric Company | Friction welded metallic turbomachinery blade element |
| US4362471A (en) * | 1974-11-29 | 1982-12-07 | Volkswagenwerk Aktiengesellschaft | Article, such as a turbine rotor and blade which comprises a first zone of a nonoxide ceramic material and a second zone of a softer material |
| US4063939A (en) * | 1975-06-27 | 1977-12-20 | Special Metals Corporation | Composite turbine wheel and process for making same |
| US4512719A (en) * | 1981-07-24 | 1985-04-23 | Motoren-Un Turbinen-Union Munchen Gmbh | Hot gas wetted turbine blade |
| US4597926A (en) * | 1981-11-30 | 1986-07-01 | Tokyo Shibaura Denki Kabushiki Kaisha | Method of manufacturing radial flow turbine rotor |
| EP0139396A1 (en) * | 1983-08-29 | 1985-05-02 | Westinghouse Electric Corporation | Combustion turbine blade with varying coating |
| US5476723A (en) * | 1992-05-27 | 1995-12-19 | Societe Nationale D'etude Et De Construction De Motors D'aviation "S.N.E.C.M.A." | Coated superalloy component |
| DE4219470A1 (en) * | 1992-06-13 | 1993-12-16 | Asea Brown Boveri | Component for high temperatures, in particular turbine blade, and method for producing this component |
| EP0574727A1 (en) * | 1992-06-13 | 1993-12-22 | Asea Brown Boveri Ag | Method for the production of a high temperature-resistant element from two different materials |
| US5409781A (en) * | 1992-06-13 | 1995-04-25 | Asea Brown Boveri Ltd. | High-temperature component, especially a turbine blade, and process for producing this component |
| US20060204769A1 (en) * | 2002-12-18 | 2006-09-14 | Alessandro Coppola | Manufacturing method for obtaining high-performance components for gas turbines and components thus obtained |
| US11261742B2 (en) | 2013-11-19 | 2022-03-01 | Raytheon Technologies Corporation | Article having variable composition coating |
| US11834963B2 (en) | 2013-11-19 | 2023-12-05 | Rtx Corporation | Article having variable composition coating |
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