US2236426A - Turbine blade - Google Patents

Turbine blade Download PDF

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Publication number
US2236426A
US2236426A US285822A US28582239A US2236426A US 2236426 A US2236426 A US 2236426A US 285822 A US285822 A US 285822A US 28582239 A US28582239 A US 28582239A US 2236426 A US2236426 A US 2236426A
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Prior art keywords
blade
section
fore
main section
passage
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Expired - Lifetime
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US285822A
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Faber Paul
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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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    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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

Definitions

  • This invention relates to turbine blades and particularly to gas turbine blades of the type in which a stream of a cooling fluid, such as cool air, flows over the surface of the blade as aprotection against overheating by the hot gases.
  • a cooling fluid such as cool air
  • An object of the present invention is to provid gas turbine blades having a main section and a leading edge or fore section to which a cooling fluid is supplied, the-passage for the cooling fluid and the openings for discharging the fluid at the blade surface being in the fore section or, alternatively, between the main and fore section of the blade.
  • An object is to provide a blade having a main section and a fore section that is of harder metal than the main section, there being an air passage and outlet slits in the fore section or between the fore section and the main section.
  • An object is to provide a turbine blade having a main section and a fore section, of crescent shape in cross-section, that serves as the leading edge of the blade and is spaced from the main section to form an air passage and outlet slits between the main section and the fore section.
  • Fig. 1 is a transverse section through a turbine 4 blade embodying the invention
  • Figs. 2, 3 and 4 are fragmentary elevational views, with parts in .section, of different forms of multl-part blades and mountings therefor;
  • Fig. 5 is a transverse section through another 45 form of blade
  • Fig. 6 is a transverse section through the root of the fore section of the blade shown in Fig. 5;
  • Fig. 7 is a transverse section through another embodiment in which the air p sage is formed, in part, by a longitudinal groove in the main sec tion of the blade.
  • the turbine blade is formed by a solid main section I and a fore section 2 that is of approximately crescent shape that constitutes the leading edge of the blade.
  • the curvatures of the adjacent longitudinal surfaces of the two blade sections are such that a passage 3 is formed between the sections and outlet slits l are provided along each side of the blade.
  • Cooling fluid that is supplied to the passage 3 will flow out through the slits l, as indicated by the lines a, to protect the main section of the blade from the hot gas that travels along the path indicated by the broken lines b.
  • the main section may be formed from the materials customarily employed but the fore section 2 is preferably formed of a particularly hard metal, such as Stellite," chrome-nickel-tungsten steel or the like that can resist erosion by the dust and cinders in the gas.
  • the composite blade may be either a moving blade or a stationary guide blade. I
  • the main section! is provided with the usual pressedor milled projecting base 5 for engagement by the flanged parts 6 that mount the blades in the undercut groove of a blade carrier 1.
  • the fore section 2 must be mounted in such manner that the cooling fluid may be supplied to they passage 3 in the blade from a channel 8
  • the v in the blade carrier. fore section 2 is of the same cross-section throughout its length and is coextensive with the main section I and its mounting flange 5.
  • Section 2 is secured to the main section I by longitudinal welds 9 that close the slits 4 at the part of the blade that lies within the blade groove, and by weld metal it that forms an ex tension of the cover I! that is welded across the outer end of the passage 3.
  • the fore section 2' is provided with an end flange I2 which is engaged by the flanged parts 6 that lie between adjacent blades.
  • the construction in other respects is like that shown in Fig. 2.
  • the base flanges may be omitted from both the main section I, and the fore section 2 of the blade, and each section secured to the mounting pieces 6 by weld metal l3.
  • the air passage and outlet slits may be formed entirely within the fore section 2a, Fig. 5, that has outer and inner curved walls ll, l5 that are joined by a longitudinal rib IS.
  • the rib l6 terminates at the ring groove of the blade carrier and the inner end of the fore section is tubular, see Fig. 6.
  • the section 2a is well cooled by the air flow and by the transfer of heat through rib l6 and the inner wall l5 to the main section I of the blade.
  • the inner surface of the wall portion I! conforms to the outer surface of the main section I and the parts may be brazed or welded to each other.
  • the wall thickness of the fore section 2 may be reduced, Fig. '7, and a longitudinal groove ll formed in the forward edge of the main section la.
  • This construction has the advantage of low cost as the erosion-resistant metal of the fore section is quite expensive and it would not be economical to enlarge the fore section to provide a large air passage.
  • a blade comprising a main section and a fore section in advance of the main section and constituting the leading edge of the blade, a blade carrier having a groove for receiving blades and a channel for cooling fluid opening into said groove, a passage extending longitudinally of said fore section and open through a longitudinal slit to one side of the blade, means mounting the inner ends of said blade sections in the groove of said blade carrier with the passage of said fore section in direct communication with the channel of said blade carrier.
  • a blade comprising a solid main section and a fore section of approximately crescent shape in transverse cross-section, means securing said sections to and spaced from each other to provide a longitudinal slot along each side of the blade and a longitudinal passage between the blade sections, and means closing the outer end of said passage, whereby a flow of'cooling fluid may be established along the surface of the main section of the blade when said blade is mounted on a blade carrier having a channel therein for supplying cooling iluid to the blade passage.
  • said securing ⁇ means comprises weld metal filling said slots at that portion of the blade which is to be seated within the blade groove of a blade carrier.
  • said securing means comprises mounting parts mechanically secured to the inner ends of said blade sections at the outer circumference thereof, said mounting parts serving to secure the blade to a blade carrier.
  • a turbine blade comprising a main section and a hollow fore section, said tore section having an inner and an outer curved wall whose longitudinal edges are spaced apart to form a longitudinal slot at each side of the blade, a rib extending longitudinally of and joining said walls, and cover means joining the outer ends of said walls, the inner surface of the inner wall conforming to and secured to the forward surface of the main section of the blade, and the inner end of the fore section being tubular and open to the spaces between theinner and outer walls at opposite sides of the longitudinal rib for supplying cooling fluid to said spaces for discharge through said longitudinal slots.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

March 25, 1941. P, FAB R 2,236,426
TURBINE BLADE Filed July 21, 1959 Patented Mar. 1941 PATENT omce tiengesellschaft Brown Switzerland Boverl & Cie, Baden,
Application Jilly 21, 1939, Serial No. 285,822
In Germany July27, 1938 7 Claims. ((1 60-41) This invention relates to turbine blades and particularly to gas turbine blades of the type in which a stream of a cooling fluid, such as cool air, flows over the surface of the blade as aprotection against overheating by the hot gases.
Hollow blades with outlet openings along the center of the leading edge of the blade have been used but this location of the outlet opening or slit has the disadvantage that the slit may be clogged by dust, cinders or other foreign matter in the high temperature gas. According to another prior design, the outlet slit or slits have been at the sides of a hollow blade, but the thin blades r and blade parts were eroded in a short time by the unavoidable impurities in the gas.
An object of the present invention is to provid gas turbine blades having a main section and a leading edge or fore section to which a cooling fluid is supplied, the-passage for the cooling fluid and the openings for discharging the fluid at the blade surface being in the fore section or, alternatively, between the main and fore section of the blade. An object is to provide a blade having a main section and a fore section that is of harder metal than the main section, there being an air passage and outlet slits in the fore section or between the fore section and the main section. An object is to provide a turbine blade having a main section and a fore section, of crescent shape in cross-section, that serves as the leading edge of the blade and is spaced from the main section to form an air passage and outlet slits between the main section and the fore section.
These and other objects and advantages of the invention will be apparent from the following specification when taken with the accompanying drawing in which:
Fig. 1 is a transverse section through a turbine 4 blade embodying the invention;
Figs. 2, 3 and 4 are fragmentary elevational views, with parts in .section, of different forms of multl-part blades and mountings therefor;
Fig. 5 is a transverse section through another 45 form of blade;-
Fig. 6 is a transverse section through the root of the fore section of the blade shown in Fig. 5; and
Fig. 7 is a transverse section through another embodiment in which the air p sage is formed, in part, by a longitudinal groove in the main sec tion of the blade.
As shown in Figs. 1 to 4, the turbine blade is formed by a solid main section I and a fore section 2 that is of approximately crescent shape that constitutes the leading edge of the blade. The curvatures of the adjacent longitudinal surfaces of the two blade sections are such that a passage 3 is formed between the sections and outlet slits l are provided along each side of the blade.
Cooling fluid that is supplied to the passage 3 will flow out through the slits l, as indicated by the lines a, to protect the main section of the blade from the hot gas that travels along the path indicated by the broken lines b. The main section may be formed from the materials customarily employed but the fore section 2 is preferably formed of a particularly hard metal, such as Stellite," chrome-nickel-tungsten steel or the like that can resist erosion by the dust and cinders in the gas. The composite blade may be either a moving blade or a stationary guide blade. I
The main section! is provided with the usual pressedor milled projecting base 5 for engagement by the flanged parts 6 that mount the blades in the undercut groove of a blade carrier 1. The fore section 2 must be mounted in such manner that the cooling fluid may be supplied to they passage 3 in the blade from a channel 8 As shown in Fig. 2, the v in the blade carrier. fore section 2 is of the same cross-section throughout its length and is coextensive with the main section I and its mounting flange 5. Section 2 is secured to the main section I by longitudinal welds 9 that close the slits 4 at the part of the blade that lies within the blade groove, and by weld metal it that forms an ex tension of the cover I! that is welded across the outer end of the passage 3.
As shown in Fig. 3, the fore section 2' is provided with an end flange I2 which is engaged by the flanged parts 6 that lie between adjacent blades. The construction in other respects is like that shown in Fig. 2. As shown in Fig. 4, the base flanges may be omitted from both the main section I, and the fore section 2 of the blade, and each section secured to the mounting pieces 6 by weld metal l3.
The air passage and outlet slits may be formed entirely within the fore section 2a, Fig. 5, that has outer and inner curved walls ll, l5 that are joined by a longitudinal rib IS. The rib l6 terminates at the ring groove of the blade carrier and the inner end of the fore section is tubular, see Fig. 6. The section 2a is well cooled by the air flow and by the transfer of heat through rib l6 and the inner wall l5 to the main section I of the blade. The inner surface of the wall portion I! conforms to the outer surface of the main section I and the parts may be brazed or welded to each other.
When air passages of large size are required, the wall thickness of the fore section 2 may be reduced, Fig. '7, and a longitudinal groove ll formed in the forward edge of the main section la. This construction has the advantage of low cost as the erosion-resistant metal of the fore section is quite expensive and it would not be economical to enlarge the fore section to provide a large air passage.
It is to be understood that the invention is not restricted to the particular constructions herein shown and described as changes may be made in the design, shape and relation of the parts without departing from the spirit of my invention as set forth in the following claims.
I claim:
1. In a turbine blade construction for high temperature gas turbines, a blade comprising a main section and a fore section in advance of the main section and constituting the leading edge of the blade, a blade carrier having a groove for receiving blades and a channel for cooling fluid opening into said groove, a passage extending longitudinally of said fore section and open through a longitudinal slit to one side of the blade, means mounting the inner ends of said blade sections in the groove of said blade carrier with the passage of said fore section in direct communication with the channel of said blade carrier.
2. In a turbine blade construction, the invention as claimed in claim 1, wherein said fore section is of an erosion-resisting metal.
3. In a turbine blade construction, a blade comprising a solid main section and a fore section of approximately crescent shape in transverse cross-section, means securing said sections to and spaced from each other to provide a longitudinal slot along each side of the blade and a longitudinal passage between the blade sections, and means closing the outer end of said passage, whereby a flow of'cooling fluid may be established along the surface of the main section of the blade when said blade is mounted on a blade carrier having a channel therein for supplying cooling iluid to the blade passage.
4. In a turbine blade construction, the invention as claimed in claim 3, wherein said securing \means comprises weld metal filling said slots at that portion of the blade which is to be seated within the blade groove of a blade carrier.
5. In a turbine blade construction, the invention as claimed in claim 3, wherein said securing means comprises mounting parts mechanically secured to the inner ends of said blade sections at the outer circumference thereof, said mounting parts serving to secure the blade to a blade carrier.
6. In a turbine blade construction, the invention as claimed in claim 3 wherein the forward edge of the main section of the blade is longitudinally grooved.
7. A turbine blade comprising a main section and a hollow fore section, said tore section having an inner and an outer curved wall whose longitudinal edges are spaced apart to form a longitudinal slot at each side of the blade, a rib extending longitudinally of and joining said walls, and cover means joining the outer ends of said walls, the inner surface of the inner wall conforming to and secured to the forward surface of the main section of the blade, and the inner end of the fore section being tubular and open to the spaces between theinner and outer walls at opposite sides of the longitudinal rib for supplying cooling fluid to said spaces for discharge through said longitudinal slots.
PAUL FABER.
US285822A 1938-07-27 1939-07-21 Turbine blade Expired - Lifetime US2236426A (en)

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Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2479777A (en) * 1943-05-22 1949-08-23 Lockheed Aircraft Corp Fuel injection means for gas turbine power plants for aircraft
US2489683A (en) * 1943-11-19 1949-11-29 Edward A Stalker Turbine
US2506581A (en) * 1945-06-30 1950-05-09 Jr Albon C Cowles Means for cooling gas turbine blades
US2563269A (en) * 1943-05-22 1951-08-07 Lockheed Aircraft Corp Gas turbine
US2567249A (en) * 1943-11-19 1951-09-11 Edward A Stalker Gas turbine
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade
US2585871A (en) * 1945-10-22 1952-02-12 Edward A Stalker Turbine blade construction with provision for cooling
US2613910A (en) * 1947-01-24 1952-10-14 Edward A Stalker Slotted turbine blade
US2647586A (en) * 1945-07-30 1953-08-04 Smith Corp A O Wide hollow steel propeller blade and method of making the same
US2653446A (en) * 1948-06-05 1953-09-29 Lockheed Aircraft Corp Compressor and fuel control system for high-pressure gas turbine power plants
US2658718A (en) * 1944-12-22 1953-11-10 Power Jets Res & Dev Ltd Manufacture and attachment of turbine and like blading
US2665881A (en) * 1948-06-15 1954-01-12 Chrysler Corp Cooled turbine blade
US2687278A (en) * 1948-05-26 1954-08-24 Chrysler Corp Article with passages
US2696364A (en) * 1948-07-08 1954-12-07 Thompson Prod Inc Turbine bucket
US2701120A (en) * 1945-10-22 1955-02-01 Edward A Stalker Turbine blade construction with provision for cooling
US2750147A (en) * 1947-10-28 1956-06-12 Power Jets Res & Dev Ltd Blading for turbines and like machines
US2780435A (en) * 1953-01-12 1957-02-05 Jackson Thomas Woodrow Turbine blade cooling structure
US2807434A (en) * 1952-04-22 1957-09-24 Gen Motors Corp Turbine rotor assembly
US2823892A (en) * 1952-06-09 1958-02-18 Gen Motors Corp Turbine buckets
US2863633A (en) * 1952-04-19 1958-12-09 Stalker Dev Company Hollow blades and manufacture thereof
US2866618A (en) * 1953-02-13 1958-12-30 Thomas W Jackson Reverse flow air cooled turbine blade
US3003316A (en) * 1953-02-10 1961-10-10 Rolls Royce Cooling means for forked exhaust ducts of gas turbine engines
US3211423A (en) * 1964-05-13 1965-10-12 Gen Electric High temperature gas turbine nozzle partition
US4653983A (en) * 1985-12-23 1987-03-31 United Technologies Corporation Cross-flow film cooling passages
US4664597A (en) * 1985-12-23 1987-05-12 United Technologies Corporation Coolant passages with full coverage film cooling slot
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US4676719A (en) * 1985-12-23 1987-06-30 United Technologies Corporation Film coolant passages for cast hollow airfoils
US4684323A (en) * 1985-12-23 1987-08-04 United Technologies Corporation Film cooling passages with curved corners
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
US4726735A (en) * 1985-12-23 1988-02-23 United Technologies Corporation Film cooling slot with metered flow
US4738588A (en) * 1985-12-23 1988-04-19 Field Robert E Film cooling passages with step diffuser
US20040035118A1 (en) * 2002-08-20 2004-02-26 Alm Development, Inc. Blade cooling in a gas turbine engine
US20110061390A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Inlet premixer for combustion apparatus
CN103476544A (en) * 2010-10-05 2013-12-25 斯奈克玛 Method for manufacturing a metal part

Cited By (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2563269A (en) * 1943-05-22 1951-08-07 Lockheed Aircraft Corp Gas turbine
US2479777A (en) * 1943-05-22 1949-08-23 Lockheed Aircraft Corp Fuel injection means for gas turbine power plants for aircraft
US2489683A (en) * 1943-11-19 1949-11-29 Edward A Stalker Turbine
US2567249A (en) * 1943-11-19 1951-09-11 Edward A Stalker Gas turbine
US2658718A (en) * 1944-12-22 1953-11-10 Power Jets Res & Dev Ltd Manufacture and attachment of turbine and like blading
US2506581A (en) * 1945-06-30 1950-05-09 Jr Albon C Cowles Means for cooling gas turbine blades
US2647586A (en) * 1945-07-30 1953-08-04 Smith Corp A O Wide hollow steel propeller blade and method of making the same
US2585871A (en) * 1945-10-22 1952-02-12 Edward A Stalker Turbine blade construction with provision for cooling
US2701120A (en) * 1945-10-22 1955-02-01 Edward A Stalker Turbine blade construction with provision for cooling
US2613910A (en) * 1947-01-24 1952-10-14 Edward A Stalker Slotted turbine blade
US2750147A (en) * 1947-10-28 1956-06-12 Power Jets Res & Dev Ltd Blading for turbines and like machines
US2687278A (en) * 1948-05-26 1954-08-24 Chrysler Corp Article with passages
US2653446A (en) * 1948-06-05 1953-09-29 Lockheed Aircraft Corp Compressor and fuel control system for high-pressure gas turbine power plants
US2665881A (en) * 1948-06-15 1954-01-12 Chrysler Corp Cooled turbine blade
US2696364A (en) * 1948-07-08 1954-12-07 Thompson Prod Inc Turbine bucket
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade
US2863633A (en) * 1952-04-19 1958-12-09 Stalker Dev Company Hollow blades and manufacture thereof
US2807434A (en) * 1952-04-22 1957-09-24 Gen Motors Corp Turbine rotor assembly
US2823892A (en) * 1952-06-09 1958-02-18 Gen Motors Corp Turbine buckets
US2780435A (en) * 1953-01-12 1957-02-05 Jackson Thomas Woodrow Turbine blade cooling structure
US3003316A (en) * 1953-02-10 1961-10-10 Rolls Royce Cooling means for forked exhaust ducts of gas turbine engines
US2866618A (en) * 1953-02-13 1958-12-30 Thomas W Jackson Reverse flow air cooled turbine blade
US3211423A (en) * 1964-05-13 1965-10-12 Gen Electric High temperature gas turbine nozzle partition
US4653983A (en) * 1985-12-23 1987-03-31 United Technologies Corporation Cross-flow film cooling passages
US4664597A (en) * 1985-12-23 1987-05-12 United Technologies Corporation Coolant passages with full coverage film cooling slot
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US4676719A (en) * 1985-12-23 1987-06-30 United Technologies Corporation Film coolant passages for cast hollow airfoils
US4684323A (en) * 1985-12-23 1987-08-04 United Technologies Corporation Film cooling passages with curved corners
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
US4726735A (en) * 1985-12-23 1988-02-23 United Technologies Corporation Film cooling slot with metered flow
US4738588A (en) * 1985-12-23 1988-04-19 Field Robert E Film cooling passages with step diffuser
US6817190B2 (en) * 2002-08-20 2004-11-16 Alm Development, Inc. Blade cooling in a gas turbine engine
US20040035118A1 (en) * 2002-08-20 2004-02-26 Alm Development, Inc. Blade cooling in a gas turbine engine
US20110061390A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Inlet premixer for combustion apparatus
US20110061391A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Vortex premixer for combustion apparatus
US20110061392A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Combustion cavity layouts for fuel staging in trapped vortex combustors
US20110061395A1 (en) * 2009-09-13 2011-03-17 Kendrick Donald W Method of fuel staging in combustion apparatus
US8549862B2 (en) 2009-09-13 2013-10-08 Lean Flame, Inc. Method of fuel staging in combustion apparatus
US8689561B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Vortex premixer for combustion apparatus
US8689562B2 (en) 2009-09-13 2014-04-08 Donald W. Kendrick Combustion cavity layouts for fuel staging in trapped vortex combustors
CN103476544A (en) * 2010-10-05 2013-12-25 斯奈克玛 Method for manufacturing a metal part
CN103476544B (en) * 2010-10-05 2016-12-07 斯奈克玛 The method making metal parts

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