US2220420A - Means for cooling machine parts - Google Patents

Means for cooling machine parts Download PDF

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Publication number
US2220420A
US2220420A US255536A US25553639A US2220420A US 2220420 A US2220420 A US 2220420A US 255536 A US255536 A US 255536A US 25553639 A US25553639 A US 25553639A US 2220420 A US2220420 A US 2220420A
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United States
Prior art keywords
blade
cooling fluid
passage
cooling
machine parts
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Expired - Lifetime
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US255536A
Inventor
Meyer Adolf
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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
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage

Definitions

  • An object of thepre'sent invention is to provide a design. of machine elements such as turbine blades which will assure an eflective cooling thereof.
  • the desired distribution of the cooling fluid e. g.,
  • Fig. l is a cross section through a turbine blade designed to supply cooling fluid to the concave side of the blade.
  • Fig. 2 is a cross section of a turbine blade desurface of the blade.
  • Fig. 3 is a cross section of a turbine blade designed to distribute cooling fluid to both the concave and the convex surfaces of the blade.
  • FIGs. 4, 5 and 6 are cross sections of modified constructions of blades similar to that illustrated in Fig. 3.
  • Fig. '7 is a longitudinal section through a turbine blade and its mounting and 5
  • Fig. 8 is a horizontal section on the line 8-8 of Fig. 7.
  • the blade is formed of an integral mass of metal and the feed passage l for cooling fluid is formed by drilling aplurality 50 of communicating holes of appropriate size depending on the thickness of the blade.
  • the end of the blade consists of a fin 2 starting at the edge of the convex side of the blade and bent over in a half circle toward the edge of the con- 55 cave side thereby forming the distribution passigned to distribute cooling fluid to the convex sage 3 which is connected to the feed passage 1 by the orifices S.
  • the free edge of the curved over fin 2 is spaced a short distance from the body of the blade leaving the slot 5 for the delivery of the cooling fluid to the concave surface 5 of the blade.
  • Fig, 2 shows a similar blade formed of an integral body of metal and provided with a cooling fluid feed passage l formed by a single drill hole through the blade.
  • the end of the blade is 10 formed by the bent over fin 2 the base of which, however, starts from the concave side of the blade and the free edge of which is adjacent the convex side of the blade.
  • the original position of the. fin 2 is shown in dot and dash lines. 15
  • Passage 3 orifice 4 and slot 5 are the same as in Fig. 1 excepting of course that slot 5 is located to discharge cooling fluid on the convex surface of the blade.
  • the blade illustrated in Fig. 3 is formed of 20 sheet material so that the cooling fluid feed passage l occupies the entire inner space of the blade enclosed by the wall which is of substantially uniform thickness.
  • the blade is designed to cool both the convex and the concave surfaces by the provision of the dome shaped hood 6 supported by.the central fin 1.
  • the hood 6 and fin! together with the body of the blade enclose the two distribution passages 8, 8 which communicate with the feed passage I through the orifices 9, 9. Slots [0, l0 discharge the cooling fluid onto the convex and concave surfaces of the blade.
  • the blade shown by Fig. 4 is similar in construction to that of Fig. 3 excepting that the central iln I of Fig. 3 is replaced by the two spaced fins-l I, l I which are integral with the side walls of the blade.
  • This construction divides the hood 6 into two parts with the orifice l2 between them which serve to discharge cooling fluid over the outer surface of the divided hood. 40
  • This cooling fluid not only effectively cools the incident edge of the blade at the line of impact of the hot impelling fluid but also aids the cooling of the side walls of the blade by the cooling fluid issuing through orifices III, In.
  • the blade of Fig. 4 is an extremely simple construction which may be made by simple bending of sheet metal.
  • the blade of Fig. 5 is similar to that ofFig. 4 excepting that the orifice I2 is closed by bringing the adjacent .walls' cf the fins II, II together and welding at. l3.
  • Fig. 7 shows the mounting of one of the blades
  • I is the feed passage through the blade
  • I 6 the distribution passage for the delivery of the cooling fluid corresponding to passage 3 of Figs. 1 and 2 or the passages 8, 8 of Figs. 3-6, l1, I! are orifices connecting passages! and l6,
  • I8 is the wall enclosing passage I 6 and corresponding to member 2 of Figs. 1 and 2 or member 6 of Figs. 3-6.
  • the wall I 8 and the opposite edge of the blade I9 are cut away leaving only the wall which encloses the passage I. This simplifies the shape of the base of the blade which is to be secured to the stator or rotor.
  • This end of the blade is inserted through an opening in the plate 20 and is secured thereto by the welding or soldering metal 2
  • the resulting structure is set into the groove or depression 22 in the rotor or stator 23 and secured therein by the welding or soldering metal 24.
  • the passage I within the vane is supplied with cooling fluid through the groove 25 and the drill holes 26 in the wall of the rotor or stator.
  • any other suitable means for delivering cooling fluid to the groove 25 may be employed.
  • the cooling fluid may be supplied under suitable pressure by a multistage fan or blower.
  • Fig. 8 which is a section on the line -88 of Fig. 7, looking downward, indicates the location of the cut away portions l8 and IQ of the blade in dot and dash lines.
  • a turbine blade comprising a body portion having two side surfaces, a passage extending partly throug '1 said body portion, a rounded leading edge portion extending along one side of said body portion, parallel passages in said leading edge portion, a duct extending between said parallel passages from said first passage to the surface of said rounded leading edge portion, holes connecting said first passage with each of said parallel passages and orifices in the outer wall of each of said parallel passages directed toward the adjacent side surface of said blade.

Description

Nov. 5, 1940. A. MEYER MEANS FOR COOLING MACHINE PARTS Filed Feb. 9, 1939 2 Sheets-Sheet l Nov. 5, 1940. A. MEYER MEANS FOR COOLING MACHINE PARTS 2 sheets-shet 2 Filed Feb. 9, 1939 Patented Nov. 5, 1940 S FOR COOLING MACHINE PARTS Adolf Meyer, Kusnacht, near Zurich, Switzerland, assignor to A'ktiengesellschaft Brown, Boveri & Cie, Baden, Switzerland, a joint-stock com- Application February 9, 1939, Serial No. 255,536
In Germany February 8, 1938 2 Claims. (01. 60-41) It has been proposed to cool turbine blades or vanes by bathing the surfaces thereof with a cooling fluid. It has further been proposed to accomplish the distribution of the cooling fluid over the vane surfaces by delivering it through a passage in the blade from which it is discharged onto a surface of the blade through a slot or orifice. Experience has shown, however, that it is very dificult to secure an effective distribution of the cooling fluid in this way. The end of the blade particularly which needs cooling the most generally receives an insufficient supply of the cooling fluid 'due to the fall in pressure of the cooling fluid along the supply passage.
An object of thepre'sent invention is to provide a design. of machine elements such as turbine blades which will assure an eflective cooling thereof. According to the present invention the desired distribution of the cooling fluid, e. g.,
air, is obtained by the provision of two types of passages one of which feeds the cooling fluid through the machine element and is connected to the distribution passage which serves to distribute the cooling fluid over the desired portion 5 of the element through suitable holes or slots the dimensions and distribution of which deter-. mine the distribution of the fluid.
The above statement of the invention will be more readily understood by reference to the ac- 30 companying drawings in which Fig. l is a cross section through a turbine blade designed to supply cooling fluid to the concave side of the blade.
Fig. 2 is a cross section of a turbine blade desurface of the blade.
Fig. 3 is a cross section of a turbine blade designed to distribute cooling fluid to both the concave and the convex surfaces of the blade.
40 Figs. 4, 5 and 6 are cross sections of modified constructions of blades similar to that illustrated in Fig. 3. Fig. '7 is a longitudinal section through a turbine blade and its mounting and 5 Fig. 8 is a horizontal section on the line 8-8 of Fig. 7.
Referring to Fig. 1 the blade is formed of an integral mass of metal and the feed passage l for cooling fluid is formed by drilling aplurality 50 of communicating holes of appropriate size depending on the thickness of the blade. The end of the blade consists of a fin 2 starting at the edge of the convex side of the blade and bent over in a half circle toward the edge of the con- 55 cave side thereby forming the distribution passigned to distribute cooling fluid to the convex sage 3 which is connected to the feed passage 1 by the orifices S. 'The free edge of the curved over fin 2 is spaced a short distance from the body of the blade leaving the slot 5 for the delivery of the cooling fluid to the concave surface 5 of the blade. I
Fig, 2 shows a similar blade formed of an integral body of metal and provided with a cooling fluid feed passage l formed by a single drill hole through the blade. The end of the blade is 10 formed by the bent over fin 2 the base of which, however, starts from the concave side of the blade and the free edge of which is adjacent the convex side of the blade. The original position of the. fin 2 is shown in dot and dash lines. 15
Passage 3, orifice 4 and slot 5 are the same as in Fig. 1 excepting of course that slot 5 is located to discharge cooling fluid on the convex surface of the blade.
The blade illustrated in Fig. 3 is formed of 20 sheet material so that the cooling fluid feed passage l occupies the entire inner space of the blade enclosed by the wall which is of substantially uniform thickness. The blade is designed to cool both the convex and the concave surfaces by the provision of the dome shaped hood 6 supported by.the central fin 1. The hood 6 and fin! together with the body of the blade enclose the two distribution passages 8, 8 which communicate with the feed passage I through the orifices 9, 9. Slots [0, l0 discharge the cooling fluid onto the convex and concave surfaces of the blade.
The blade shown by Fig. 4 is similar in construction to that of Fig. 3 excepting that the central iln I of Fig. 3 is replaced by the two spaced fins-l I, l I which are integral with the side walls of the blade. This construction divides the hood 6 into two parts with the orifice l2 between them which serve to discharge cooling fluid over the outer surface of the divided hood. 40 This cooling fluid not only effectively cools the incident edge of the blade at the line of impact of the hot impelling fluid but also aids the cooling of the side walls of the blade by the cooling fluid issuing through orifices III, In. It will be noted also that the blade of Fig. 4 is an extremely simple construction which may be made by simple bending of sheet metal.
The blade of Fig. 5 is similar to that ofFig. 4 excepting that the orifice I2 is closed by bringing the adjacent .walls' cf the fins II, II together and welding at. l3. I i
In the construction illustrated in Fig. 6 which is functionally similar to that of Fig. 5, the two I side walls of the blade are formed by welding together two properly shaped sheets of metal. The welds appear at I4 and I5.
Fig. 7 shows the mounting of one of the blades,
the figure being a longitudinal section through the blade. I is the feed passage through the blade, I 6 the distribution passage for the delivery of the cooling fluid corresponding to passage 3 of Figs. 1 and 2 or the passages 8, 8 of Figs. 3-6, l1, I! are orifices connecting passages! and l6, I8 is the wall enclosing passage I 6 and corresponding to member 2 of Figs. 1 and 2 or member 6 of Figs. 3-6. As shown in Fig. 7, at the open end of the blade the wall I 8 and the opposite edge of the blade I9 are cut away leaving only the wall which encloses the passage I. This simplifies the shape of the base of the blade which is to be secured to the stator or rotor. This end of the blade is inserted through an opening in the plate 20 and is secured thereto by the welding or soldering metal 2|. The resulting structure is set into the groove or depression 22 in the rotor or stator 23 and secured therein by the welding or soldering metal 24. The passage I within the vane is supplied with cooling fluid through the groove 25 and the drill holes 26 in the wall of the rotor or stator. In place of drill holes 26 which communicate with a chamber through which cooling fluid is supplied any other suitable means for delivering cooling fluid to the groove 25 may be employed. The cooling fluid may be supplied under suitable pressure by a multistage fan or blower.
Fig. 8 which is a section on the line -88 of Fig. 7, looking downward, indicates the location of the cut away portions l8 and IQ of the blade in dot and dash lines.
I claim:
l. A turbine blade comprising a body portion having two side surfaces, a passage extending partly throug '1 said body portion, a rounded leading edge portion extending along one side of said body portion, parallel passages in said leading edge portion, a duct extending between said parallel passages from said first passage to the surface of said rounded leading edge portion, holes connecting said first passage with each of said parallel passages and orifices in the outer wall of each of said parallel passages directed toward the adjacent side surface of said blade.
2. A turbine blade-comprising a body portion, a relatively sharp trailing edge portion and an opposite rounded leading edge portion, a passage in said'body portion and a communicating passage in said rounded leading edge portion for conveying cooling gas, a part of said sharp trailing edge portion and a part of said rounded leading edge portion being cut away leaving only the wall of the passage in said body portion at one end thereof as a foot member for the mounting of the blade, an orifice in the wall of the passage in said rounded leading edge portion for de- -livering cooling gas to a face of said body portion, a portion only of said foot member being embedded in a rotor or stator leaving an orifice between an end of the rounded leading end portion and the surface of the rotor or stator for the flow of cooling gas to cool said foot member.
ADOLF MEYER.
US255536A 1938-02-08 1939-02-09 Means for cooling machine parts Expired - Lifetime US2220420A (en)

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GB (1) GB524794A (en)

Cited By (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2463340A (en) * 1945-02-22 1949-03-01 Wiberg Oscar Anton Axial flow turbine blade structure
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
US2559131A (en) * 1948-04-22 1951-07-03 Oestrich Hollow blade for gas turbines and the like
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
US2585871A (en) * 1945-10-22 1952-02-12 Edward A Stalker Turbine blade construction with provision for cooling
US2613911A (en) * 1947-11-06 1952-10-14 Stalker Dev Company Fluid turning blade
US2613910A (en) * 1947-01-24 1952-10-14 Edward A Stalker Slotted turbine blade
US2625366A (en) * 1948-11-18 1953-01-13 Packard Motor Car Co Turbine rotor construction
US2641439A (en) * 1947-10-01 1953-06-09 Chrysler Corp Cooled turbine or compressor blade
US2641440A (en) * 1947-11-18 1953-06-09 Chrysler Corp Turbine blade with cooling means and carrier therefor
US2658718A (en) * 1944-12-22 1953-11-10 Power Jets Res & Dev Ltd Manufacture and attachment of turbine and like blading
US2687278A (en) * 1948-05-26 1954-08-24 Chrysler Corp Article with passages
US2700530A (en) * 1948-08-27 1955-01-25 Chrysler Corp High temperature elastic fluid apparatus
US2750147A (en) * 1947-10-28 1956-06-12 Power Jets Res & Dev Ltd Blading for turbines and like machines
DE1000733B (en) * 1953-10-21 1957-01-10 Wilhelm Ludowici Dr Ing Car-shaped kiln for pottery
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
US2858100A (en) * 1952-02-01 1958-10-28 Stalker Dev Company Blade structure for turbines and the like
US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
US3032314A (en) * 1957-05-28 1962-05-01 Snecma Method of and device for cooling the component elements of machines
US3112557A (en) * 1958-02-10 1963-12-03 Rolls Royce Turbine and compressor blades
US3319593A (en) * 1962-12-24 1967-05-16 Papst Hermann Boundary layer control
US4026659A (en) * 1975-10-16 1977-05-31 Avco Corporation Cooled composite vanes for turbine nozzles
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
US4672727A (en) * 1985-12-23 1987-06-16 United Technologies Corporation Method of fabricating film cooling slot in a hollow airfoil
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
US4770608A (en) * 1985-12-23 1988-09-13 United Technologies Corporation Film cooled vanes and turbines
US4859147A (en) * 1988-01-25 1989-08-22 United Technologies Corporation Cooled gas turbine blade
US5097660A (en) * 1988-12-28 1992-03-24 Sundstrand Corporation Coanda effect turbine nozzle vane cooling
US6241468B1 (en) 1998-10-06 2001-06-05 Rolls-Royce Plc Coolant passages for gas turbine components
US6589600B1 (en) * 1999-06-30 2003-07-08 General Electric Company Turbine engine component having enhanced heat transfer characteristics and method for forming same
US20060102789A1 (en) * 2002-07-18 2006-05-18 Schmidt Eric T Linear shock wave absorber
US20080253884A1 (en) * 2007-04-12 2008-10-16 United Technologies Corporation Out-flow margin protection for a gas turbine engine
US8246297B2 (en) 2008-07-21 2012-08-21 Pratt & Whitney Canada Corp. Shroud segment cooling configuration
US20210332705A1 (en) * 2020-04-27 2021-10-28 Raytheon Technologies Corporation Airfoil with cmc liner and multi-piece monolithic ceramic shell

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE767546C (en) * 1938-09-12 1952-11-04 Bmw Flugmotorenbau G M B H Internally cooled turbine blade
DE969599C (en) * 1943-05-27 1958-06-19 Holzwarth Gasturbinen G M B H Cooled nozzle body for centrifugal machines, especially exhaust gas turbines
DE1024754B (en) * 1956-02-11 1958-02-20 Maschf Augsburg Nuernberg Ag Cooled blade for hot operated turbines or compressors
GB2202907A (en) * 1987-03-26 1988-10-05 Secr Defence Cooled aerofoil components

Cited By (49)

* 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
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
US2463340A (en) * 1945-02-22 1949-03-01 Wiberg Oscar Anton Axial flow turbine blade structure
US2506581A (en) * 1945-06-30 1950-05-09 Jr Albon C Cowles Means for cooling gas turbine blades
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
US2641439A (en) * 1947-10-01 1953-06-09 Chrysler Corp Cooled turbine or compressor blade
US2750147A (en) * 1947-10-28 1956-06-12 Power Jets Res & Dev Ltd Blading for turbines and like machines
US2613911A (en) * 1947-11-06 1952-10-14 Stalker Dev Company Fluid turning blade
US2641440A (en) * 1947-11-18 1953-06-09 Chrysler Corp Turbine blade with cooling means and carrier therefor
US2559131A (en) * 1948-04-22 1951-07-03 Oestrich Hollow blade for gas turbines and the like
US2687278A (en) * 1948-05-26 1954-08-24 Chrysler Corp Article with passages
US2700530A (en) * 1948-08-27 1955-01-25 Chrysler Corp High temperature elastic fluid apparatus
US2625366A (en) * 1948-11-18 1953-01-13 Packard Motor Car Co Turbine rotor construction
US2858100A (en) * 1952-02-01 1958-10-28 Stalker Dev Company Blade structure for turbines and the like
US2807434A (en) * 1952-04-22 1957-09-24 Gen Motors Corp Turbine rotor assembly
US2873944A (en) * 1952-09-10 1959-02-17 Gen Motors Corp Turbine blade cooling
US2780435A (en) * 1953-01-12 1957-02-05 Jackson Thomas Woodrow Turbine blade cooling structure
DE1000733B (en) * 1953-10-21 1957-01-10 Wilhelm Ludowici Dr Ing Car-shaped kiln for pottery
DE1000733C2 (en) * 1953-10-21 1957-06-19 Wilhelm Ludowici Dr Ing Car-shaped kiln for pottery
US3032314A (en) * 1957-05-28 1962-05-01 Snecma Method of and device for cooling the component elements of machines
US3112557A (en) * 1958-02-10 1963-12-03 Rolls Royce Turbine and compressor blades
US3319593A (en) * 1962-12-24 1967-05-16 Papst Hermann Boundary layer control
US4026659A (en) * 1975-10-16 1977-05-31 Avco Corporation Cooled composite vanes for turbine nozzles
EP0227579A2 (en) * 1985-12-23 1987-07-01 United Technologies Corporation Film coolant passage with swirl diffuser
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
US4672727A (en) * 1985-12-23 1987-06-16 United Technologies Corporation Method of fabricating film cooling slot in a hollow airfoil
US4676719A (en) * 1985-12-23 1987-06-30 United Technologies Corporation Film coolant passages for cast hollow airfoils
EP0227579B1 (en) * 1985-12-23 1992-01-29 United Technologies Corporation Film coolant passage with swirl diffuser
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
US4770608A (en) * 1985-12-23 1988-09-13 United Technologies Corporation Film cooled vanes and turbines
US4653983A (en) * 1985-12-23 1987-03-31 United Technologies Corporation Cross-flow film cooling passages
US4859147A (en) * 1988-01-25 1989-08-22 United Technologies Corporation Cooled gas turbine blade
US5097660A (en) * 1988-12-28 1992-03-24 Sundstrand Corporation Coanda effect turbine nozzle vane cooling
US6241468B1 (en) 1998-10-06 2001-06-05 Rolls-Royce Plc Coolant passages for gas turbine components
US6589600B1 (en) * 1999-06-30 2003-07-08 General Electric Company Turbine engine component having enhanced heat transfer characteristics and method for forming same
US20060102789A1 (en) * 2002-07-18 2006-05-18 Schmidt Eric T Linear shock wave absorber
US7357351B2 (en) * 2002-07-18 2008-04-15 Eric T. Schmidt Linear shock wave absorber
US20080253884A1 (en) * 2007-04-12 2008-10-16 United Technologies Corporation Out-flow margin protection for a gas turbine engine
US7798765B2 (en) 2007-04-12 2010-09-21 United Technologies Corporation Out-flow margin protection for a gas turbine engine
US8246297B2 (en) 2008-07-21 2012-08-21 Pratt & Whitney Canada Corp. Shroud segment cooling configuration
US20210332705A1 (en) * 2020-04-27 2021-10-28 Raytheon Technologies Corporation Airfoil with cmc liner and multi-piece monolithic ceramic shell
US11286783B2 (en) * 2020-04-27 2022-03-29 Raytheon Technologies Corporation Airfoil with CMC liner and multi-piece monolithic ceramic shell

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BE432599A (en)
FR849880A (en) 1939-12-04
GB524794A (en) 1940-08-14
CH209009A (en) 1940-03-15

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