US3191908A - Blades for fluid flow machines - Google Patents

Blades for fluid flow machines Download PDF

Info

Publication number
US3191908A
US3191908A US258445A US25844563A US3191908A US 3191908 A US3191908 A US 3191908A US 258445 A US258445 A US 258445A US 25844563 A US25844563 A US 25844563A US 3191908 A US3191908 A US 3191908A
Authority
US
United States
Prior art keywords
blade
fluid
tip
root
sinuous
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US258445A
Inventor
Powell Frederick Bowen
Petrie James Alexander
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from GB1592561A external-priority patent/GB950355A/en
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to US258445A priority Critical patent/US3191908A/en
Application granted granted Critical
Publication of US3191908A publication Critical patent/US3191908A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D5/14—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
    • F01D5/187—Convection cooling

Definitions

  • This invention concerns blades for fluid flow machines e.g, turbine rotor blades for gas turbine engines.
  • blade is used in this specification in a broad sense to include blade-like members such as nozzle guide vanes.
  • a blade adapted for use in a fluid flow machine and having formed therein a fluid conduit, said fluid conduit having an inlet through which a blade cooling fluid may be introduced into said fluid conduit and a sinuous fluid passageway which is formed in said blade and which is adapted to be supplied with a blade cooling fluid, the sinuous fluid passageway extending substantially completely around the fluid conduit and being so formed that blade cooling fluid flowing therethrough effects substantial heat-shielding of the blade cooling fluid flowing through the fluid conduit.
  • the sinuous fluid passageway is such that blade cooling fluid on entering the lattter first flow-s through leading and trailing portions of the blade and thereafter flows through the central portion of the blade.
  • leading and trailing portions i.e. the hottest portions of the blade will be cooled by the blade cooling fluid when the latter is at its coldest while the central portion of the blade, which does not require as much cooling, is cooled by the blade cooling fluid after the latter has picked up heat from the said leading and trailing portions.
  • the sinuous fluid passageway communicates with the fluid conduit so as to be supplied with blade cooling fluid therefrom.
  • the fluid conduit extends from substantially the root to the tip of the blade and the sinuous fluid passageway comprises a series of spaced fluid passages which also extend substantially from the root to the tip of the blade, said fluid passages being connected together by fluid paths which are alternatively arranged adjacent to the root and tip of the blade, one of the fluid passages communicating with the fluid conduit and another of the fluid passages having'an outlet through which blade cooling fluid may pass out of the blade, whereby blade cooling fluid which has been introduced into the fluid conduit through said inlet will flow through adjacent fluid passages in opposite directions and will finally pass out of the blade through said outlet.
  • the said inlet is preferably disposed at the root of the blade, the said outlet being disposed at the tip of the blade.
  • One of the fluid passages is preferably disposed adjacent the leading or trailing edge of the blade and communicates with the fluid conduit by way of a drilling which is disposed adjacent the mid-height of the blade whereby blade cooling fluid passing through said drilling forms a jet which cools the said leading or trailing edge adjacent the mid-height of the latter.
  • the blade is preferably formed with two fluid conduits each of which is surrounded by a sinuous fluid passageway, the two sinuous fluid passageways. respectively comprising fluid passages which are disposed adjacent the leading and trailing edges of the blade and which communicate with their respective fluid conduits by way of drilling disposed adjacent the mid-height of the blade.
  • the invention also comprises a gas turbine engine provided with a blade as set forth above.
  • FIGURE l' is a diagrammatic section through a gas turbine engine
  • FIGURE 2 is a diagrammatic elevation-cf a turbine blade of the engine of FIGURE 1,
  • FIGURE 3 is a section taken on the line 3 s of FIG-7 URE 2
  • FIGURES 4 and 5 are sections taken respectively on the lines 4-4 and 55 of FIGURE 3.
  • air which flows within the blade and towards the root thereof is, for ease of explanation, referred to as passing downwardly in the blade, while air which flows within the blade towards the tip thereof is referred to as passing upwardly in the blade.
  • a gas turbine engine 10 com prises in flow series a compressor 11, combustion equipment 12, and a turbine 13, the turbine 13 driving the corn the blade, but are of course supplied at the root of the blade with cooling air from the air inlets 17, 18.
  • the fluid conduits 20, 21 respectively communicate with fluid passages 23, 24 by way of drillings 25, 26, the
  • passages 23, 24 being respectively blanked off at the root and tip of the blade.
  • the drillings 25, 26 are disposed at the mid-height of the blade i.e. halfway between the root and the tip of the blade.
  • the fluid passages 23, 24 are respectively disposed adjacent the leading edge 27 and the trailing edge 23 of the blade. Accordingly jets of cooling air are directed through the drillings 25, 26 into the fluid passages 23, 24 soas to impinge, at mid-height, on the surfaces of the latter adjacent the leading and trailing edges 27, 28. The said jets thus effect cooling of what are, in operation, the hottest parts of the blade.
  • fluid passages 30-33% Extending longitudinally within the blade 15 from the root to the tip thereof are spaced apart fluid passages 30-33% all of which are blanked off at the root and at the tip of the blade.
  • the fluid passages 39-34 are disposed adjacent the convex orupstream side 41 of the blade, while the fluid passages 35-39'are disposed adjacent theconcave or'downstream side 42 of the blade.
  • the fluid passages 30, 39 respectively communicate with the fluid passage 23 by way of drilling 43, 44 which are respectively disposed adjacent the tip and the root of the blade.
  • the fluid communicate with the fluid passages 31, 38 by way of drillings 45, 46 which are respectively disposed adjacent 47, 48 are respectively disposed adjacent the tip and the root of the blade.
  • the fluid passages 34, 35 respectively communicate with the fluid passage 24 by way of drillings 51, 52 which are respectively disposed adjacent the root and the tip of the blade.
  • the fluid passages 34, 35 also respectively communicate with the fluid passages 33, 36 by way of drillpassages 30, 39 also respectively 45 ings 53, 54, while the fluid passages 33, 36 respectively communicate with the fluid passages 32, 37 by Way of drillings 55, 56.
  • the fluid passages 32, 37 respectively communicate, by way of drillings 57, 58, with a fluid passage 60 which extends longitudinally of the blade from the root to the tip thereof, the fluid passage 60 being blanked at the root and being open at the tip of the blade.
  • the drillings 51, 54, 55 and 58 are disposed adjacent the root of the blade, while the drillings 52, 53, 56, and 57 are disposed adjacent the tip of the blade.
  • the cooling air which has passed into the fluid conduit 20 and has entered the fluid passage 23 through the drilling 25 first impinges on the surface of the passage 23 at mid-height and thereafter divides into two portions which respectively flow downwardly and upwardly through the passage 23 towards the root and the tip of the blade.
  • the air which has flowed upwardly in the passage 23 passes through the drilling 43, flows down the passage 30, passes through the drilling 45, flows up the passage 31 and passes through the drilling 47 to the upper end of the passage 50.
  • the air which has flowed downwardly in the passage 23 passes through the drilling 44, flows up the passage 39, passes through the drilling 46, flows down the passage 38, and then passes through the drillings 48 to the lower end of the passage 50.
  • the cooling air which is thus supplied to the passage 50 passes out of the blade through the tip thereof.
  • fluid passages 23, 30, 31, 38, 39, t together with the drillings 43-48, collectively constitute a sinuous fluid pasasgeway the cooling air flowing through which eflects substantial heat-shielding of the cooling air flowing through the fluid conduit 20.
  • the blade which may be a close forging, which is subsequently machined by an electrolytic or spark process, may be formed in two halves which abut at the midchord line of the blade and are ecured together by brazing or electron beam welding.
  • the conduits, passages and drillings in the blade maybe formed by spark machining (e.g. carbon electrode spark machining) or by an electrolytic process.
  • leading and trailing edges 27, 28, which are in operation the hottest portions of the blade will be cooled by the cooling air when the latter is at its coldest, while the central portion of the blade, which does not require as much cooling, is cooled by the cooling air when the latter is at its coldest, while the central portion of the blade, which does not require as much cooling, is cooled by the cooling air after the latter has been heated by flowing through the blade.
  • a substantially uniform temperature is therefore achieved throughout the blade.
  • a blade adapted for use in a fluid flow machine said blade having a root and a tip, two fluid conduits formed in said blade and extending from substantially the root to the tip thereof, an inlet to each said fluid conduit, through which a blade cooling fluid may be introduced into said fluid conduits, two sinuous fluid passageways formed in said blade, each of said sinuous fluid passageways comprising a series of spaced fluid passages which also extend substantially from the root to the tip of the blade, fluid paths which are alternately arranged adjacent to the root and tip of the blade, connecting said fluid passages together, one fluid passage of each sinuous fluid passageway being disposed adjacent the leading and trailing edges of the blade respectively and communicating with their respective fluid conduits by way of drillings disposed adjacent the mid-height of the blade, blade cooling fluid passing through said drillings forming jets which cool the said leading and trailing edges adjacent the midheights of the blade, one fluid passage of each sinuous fluid passageway being provided with an outlet through which blade cooling fluid may pass out of the blade, each sinuous fluid passageway extending substantially completely
  • each said inlet is disposed at the root of the blade, each said outlet being disposed at the tip of the blade.
  • a blade adapted for use in a fluid flow machine said blade having a root and a tip; a fluid conduit formed in the interior of said blade and extending from the root to the tip thereof and having an inlet at one end thereof through which a blade cooling fluid is introduced therein; a sinuous fluid passageway formed in said blade and extending completely around the fluid conduit, said sinuous fluid passageway comprising a plurality of spaced fluid passages, each extending substantially from the root to the tip of the blade, said plurality of spaced fluid passages defining a pair of sinuous paths, one path being disposed adjacent the upstream side of the blade and the other path being disposed adjacent the downstream side of the blade, with one of said fluid passages being common to both sinuous paths and disposed adjacent the leading edge of the blade; said one fluid passage disposed adjacent the leading edge of the blade communicating with said fluid conduit by a drilling disposed adjacent the mid height of the blade and forming a jet through which blade cooling fluid passes from the fluid conduit into the one passage and cools the leading edge of the blade from the mid
  • a blade adapted for use in a fluid flow machine said blade having a root and a tip, a first fluid conduit formed in the interior of said blade and extending from the root to the tip thereof and having an inlet at one end thereof through which a blade cooling fluid is introduced; a first sinuous fluid passageway formed in said blade and extending completely around said first fluid conduit, said first sinuous fluid passageway comprising a plurality of spaced fluid passages, each extending substantially from the root to the tip of the blade, said plurality of spaced fluid passages defining a pair of sinuous paths, one path of said pair being disposed adjacent the upstream side of the blade and the other path of said pair being disposed adjacent the downstream side of said blade with one of said plurality of fluid passages being common to both sinuous paths and disposed adjacentthe leading edge of the blade; the said one fluid passage disposed adjacent the leading edge of the blade communicating with said fluid conduit by a drilling disposed adjacent the mid height of the blade and forming a jet through which blade cooling fluid passes from the fluid conduit into the one passage and

Landscapes

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

Description

June 29, 1965 F. B. POWELL ETAL BLADES FOR FLUID FLOW MACHINES 4 Sheets-Sheet 1 Filed Feb. 14, 1963 F/GZ,
Inve lora z By z Attorneys F. B. POWELL ETAL 3,191,908 BLADES FOR FLUID FLOW MACHINES June 29, 1965 4 Sheets-Sheet 2 Filed Feb. 14, 1963 A tlorneys United States Patent 3,191,903 BLADES EUR FLUKE) FLGW MACHINES Frederick Bowen EowelLHathern, near Loughborough,
and James Alexander Petrie, 'Littleover, Derby, England, assignors to Rolls-Royce Limited, Derby, England,
a company of Great Britain Filed Feb. 14, 1963, Ser. No, 258,445 4 Claims. (1. 25339.1'5)
This invention concerns blades for fluid flow machines e.g, turbine rotor blades for gas turbine engines.
The term blade is used in this specification in a broad sense to include blade-like members such as nozzle guide vanes. 1
According to the present invention, there is provided a blade adapted for use in a fluid flow machine and having formed therein a fluid conduit, said fluid conduit having an inlet through which a blade cooling fluid may be introduced into said fluid conduit and a sinuous fluid passageway which is formed in said blade and which is adapted to be supplied with a blade cooling fluid, the sinuous fluid passageway extending substantially completely around the fluid conduit and being so formed that blade cooling fluid flowing therethrough effects substantial heat-shielding of the blade cooling fluid flowing through the fluid conduit. 7
lreferably the sinuous fluid passageway is such that blade cooling fluid on entering the lattter first flow-s through leading and trailing portions of the blade and thereafter flows through the central portion of the blade. It will be appreciated that in such an arrangement the leading and trailing portions, i.e. the hottest portions of the blade will be cooled by the blade cooling fluid when the latter is at its coldest while the central portion of the blade, which does not require as much cooling, is cooled by the blade cooling fluid after the latter has picked up heat from the said leading and trailing portions.
Preferably the sinuous fluid passageway communicates with the fluid conduit so as to be supplied with blade cooling fluid therefrom.
Preferably the fluid conduit extends from substantially the root to the tip of the blade and the sinuous fluid passageway comprises a series of spaced fluid passages which also extend substantially from the root to the tip of the blade, said fluid passages being connected together by fluid paths which are alternatively arranged adjacent to the root and tip of the blade, one of the fluid passages communicating with the fluid conduit and another of the fluid passages having'an outlet through which blade cooling fluid may pass out of the blade, whereby blade cooling fluid which has been introduced into the fluid conduit through said inlet will flow through adjacent fluid passages in opposite directions and will finally pass out of the blade through said outlet.
' The said inlet is preferably disposed at the root of the blade, the said outlet being disposed at the tip of the blade.
One of the fluid passages is preferably disposed adjacent the leading or trailing edge of the blade and communicates with the fluid conduit by way of a drilling which is disposed adjacent the mid-height of the blade whereby blade cooling fluid passing through said drilling forms a jet which cools the said leading or trailing edge adjacent the mid-height of the latter.
. The blade is preferably formed with two fluid conduits each of which is surrounded by a sinuous fluid passageway, the two sinuous fluid passageways. respectively comprising fluid passages which are disposed adjacent the leading and trailing edges of the blade and which communicate with their respective fluid conduits by way of drilling disposed adjacent the mid-height of the blade.
ICE
The invention also comprises a gas turbine engine provided with a blade as set forth above.
The invention is illustrated, merely by way of example, in the accompanying drawings in which:
FIGURE l'is a diagrammatic section through a gas turbine engine,
FIGURE 2 is a diagrammatic elevation-cf a turbine blade of the engine of FIGURE 1,
FIGURE 3 is a section taken on the line 3 s of FIG-7 URE 2, and
FIGURES 4 and 5 are sections taken respectively on the lines 4-4 and 55 of FIGURE 3.
In the following description, air which flows within the blade and towards the root thereof is, for ease of explanation, referred to as passing downwardly in the blade, while air which flows within the blade towards the tip thereof is referred to as passing upwardly in the blade.
Referring to the drawings, a gas turbine engine 10 com prises in flow series a compressor 11, combustion equipment 12, and a turbine 13, the turbine 13 driving the corn the blade, but are of course supplied at the root of the blade with cooling air from the air inlets 17, 18.
The fluid conduits 20, 21 respectively communicate with fluid passages 23, 24 by way of drillings 25, 26, the
passages 23, 24 being respectively blanked off at the root and tip of the blade. The drillings 25, 26 are disposed at the mid-height of the blade i.e. halfway between the root and the tip of the blade.
The fluid passages 23, 24 are respectively disposed adjacent the leading edge 27 and the trailing edge 23 of the blade. Accordingly jets of cooling air are directed through the drillings 25, 26 into the fluid passages 23, 24 soas to impinge, at mid-height, on the surfaces of the latter adjacent the leading and trailing edges 27, 28. The said jets thus effect cooling of what are, in operation, the hottest parts of the blade.
Extending longitudinally within the blade 15 from the root to the tip thereof are spaced apart fluid passages 30-33% all of which are blanked off at the root and at the tip of the blade. The fluid passages 39-34 are disposed adjacent the convex orupstream side 41 of the blade, while the fluid passages 35-39'are disposed adjacent theconcave or'downstream side 42 of the blade.
The fluid passages 30, 39 respectively communicate with the fluid passage 23 by way of drilling 43, 44 which are respectively disposed adjacent the tip and the root of the blade. The fluid communicate with the fluid passages 31, 38 by way of drillings 45, 46 which are respectively disposed adjacent 47, 48 are respectively disposed adjacent the tip and the root of the blade.
The fluid passages 34, 35 respectively communicate with the fluid passage 24 by way of drillings 51, 52 which are respectively disposed adjacent the root and the tip of the blade. The fluid passages 34, 35 also respectively communicate with the fluid passages 33, 36 by way of drillpassages 30, 39 also respectively 45 ings 53, 54, while the fluid passages 33, 36 respectively communicate with the fluid passages 32, 37 by Way of drillings 55, 56. The fluid passages 32, 37 respectively communicate, by way of drillings 57, 58, with a fluid passage 60 which extends longitudinally of the blade from the root to the tip thereof, the fluid passage 60 being blanked at the root and being open at the tip of the blade.
The drillings 51, 54, 55 and 58 are disposed adjacent the root of the blade, while the drillings 52, 53, 56, and 57 are disposed adjacent the tip of the blade.
Accordingly, the cooling air which has passed into the fluid conduit 20 and has entered the fluid passage 23 through the drilling 25 first impinges on the surface of the passage 23 at mid-height and thereafter divides into two portions which respectively flow downwardly and upwardly through the passage 23 towards the root and the tip of the blade. The air which has flowed upwardly in the passage 23 passes through the drilling 43, flows down the passage 30, passes through the drilling 45, flows up the passage 31 and passes through the drilling 47 to the upper end of the passage 50.
The air which has flowed downwardly in the passage 23 passes through the drilling 44, flows up the passage 39, passes through the drilling 46, flows down the passage 38, and then passes through the drillings 48 to the lower end of the passage 50. The cooling air which is thus supplied to the passage 50 passes out of the blade through the tip thereof.
It will thus be noted that the fluid passages 23, 30, 31, 38, 39, t), together with the drillings 43-48, collectively constitute a sinuous fluid pasasgeway the cooling air flowing through which eflects substantial heat-shielding of the cooling air flowing through the fluid conduit 20.
Similarly, the cooling air which has passed into the fluid conduit 21 and has entered the fluid passage 24 through the drilling 26, impinges on the surface of the passage 24 at mid-height, and thereafter divides into two portions which respectively flow downwardly and upwardly through the passage 24 towards the root and the tip of the blade.
The air which has flowed upwardly in the passage 24'. passes through the drilling 52, flows down the passage 35, passes through the drilling 54, passes up the passage 36, passes through the drilling 56, passes down the passage 37, and passes through the drilling 58 to the lower end of the passage 69.
The air which has flowed downwardly in the passage 24 passes through the drilling 51, flows up the passage 3- passes through the drilling 53, flows down the passage 33,
passes through the drilling 5S, flows up the passage 32,
and passes through the drilling 57 to the upper end of the passage 60. The cooling air which is thus supplied to the passage 69 passes out of the blade through the tip thereof.
The fluid passages 24, 32-37, and 68, together with the drillings 51-58, collectively constitute a sinuous fluid passageway and the cooling air flowing through this sinuous fluid passageway will effect substantial heat-shielding of the cooling air flowing through the fluid conduit 21.
The blade, which may be a close forging, which is subsequently machined by an electrolytic or spark process, may be formed in two halves which abut at the midchord line of the blade and are ecured together by brazing or electron beam welding. The conduits, passages and drillings in the blade maybe formed by spark machining (e.g. carbon electrode spark machining) or by an electrolytic process.
It will be appreciated that the leading and trailing edges 27, 28, which are in operation the hottest portions of the blade, will be cooled by the cooling air when the latter is at its coldest, while the central portion of the blade, which does not require as much cooling, is cooled by the cooling air when the latter is at its coldest, while the central portion of the blade, which does not require as much cooling, is cooled by the cooling air after the latter has been heated by flowing through the blade. A substantially uniform temperature is therefore achieved throughout the blade.
We claim:
1. A blade adapted for use in a fluid flow machine said blade having a root and a tip, two fluid conduits formed in said blade and extending from substantially the root to the tip thereof, an inlet to each said fluid conduit, through which a blade cooling fluid may be introduced into said fluid conduits, two sinuous fluid passageways formed in said blade, each of said sinuous fluid passageways comprising a series of spaced fluid passages which also extend substantially from the root to the tip of the blade, fluid paths which are alternately arranged adjacent to the root and tip of the blade, connecting said fluid passages together, one fluid passage of each sinuous fluid passageway being disposed adjacent the leading and trailing edges of the blade respectively and communicating with their respective fluid conduits by way of drillings disposed adjacent the mid-height of the blade, blade cooling fluid passing through said drillings forming jets which cool the said leading and trailing edges adjacent the midheights of the blade, one fluid passage of each sinuous fluid passageway being provided with an outlet through which blade cooling fluid may pass out of the blade, each sinuous fluid passageway extending substantially completely around the respective fluid conduit.
2. A blade as claimed in claim 1 in which each said inlet is disposed at the root of the blade, each said outlet being disposed at the tip of the blade.
3. A blade adapted for use in a fluid flow machine, said blade having a root and a tip; a fluid conduit formed in the interior of said blade and extending from the root to the tip thereof and having an inlet at one end thereof through which a blade cooling fluid is introduced therein; a sinuous fluid passageway formed in said blade and extending completely around the fluid conduit, said sinuous fluid passageway comprising a plurality of spaced fluid passages, each extending substantially from the root to the tip of the blade, said plurality of spaced fluid passages defining a pair of sinuous paths, one path being disposed adjacent the upstream side of the blade and the other path being disposed adjacent the downstream side of the blade, with one of said fluid passages being common to both sinuous paths and disposed adjacent the leading edge of the blade; said one fluid passage disposed adjacent the leading edge of the blade communicating with said fluid conduit by a drilling disposed adjacent the mid height of the blade and forming a jet through which blade cooling fluid passes from the fluid conduit into the one passage and cools the leading edge of the blade from the mid height outwardly toward the root and tip respectively; drillings in said blade alternately arranged adjacent to the root and tip of the blade and connecting said fluid passages of each sinuous path together and with the one common fluid passage disposed adjacent the leading edge; and another of said fluid passages being common to both of the sinuous fluid paths and connected thereto by drillings respectively disposed alternately adjacent the root and tip of the blade, said another fluid passage being disposed on an opposite side of the fluid conduit with respect to the one fluid passage adjacent the leading edge and having an outlet for the blade cooling fluid at one end thereof.
4. A blade adapted for use in a fluid flow machine, said blade having a root and a tip, a first fluid conduit formed in the interior of said blade and extending from the root to the tip thereof and having an inlet at one end thereof through which a blade cooling fluid is introduced; a first sinuous fluid passageway formed in said blade and extending completely around said first fluid conduit, said first sinuous fluid passageway comprising a plurality of spaced fluid passages, each extending substantially from the root to the tip of the blade, said plurality of spaced fluid passages defining a pair of sinuous paths, one path of said pair being disposed adjacent the upstream side of the blade and the other path of said pair being disposed adjacent the downstream side of said blade with one of said plurality of fluid passages being common to both sinuous paths and disposed adjacentthe leading edge of the blade; the said one fluid passage disposed adjacent the leading edge of the blade communicating with said fluid conduit by a drilling disposed adjacent the mid height of the blade and forming a jet through which blade cooling fluid passes from the fluid conduit into the one passage and cools the leading edge of the blade from the mid height outwardly toward the root and tip respectively, drillings in said blade alternately arranged adjacent the root and tip of the blade and connecting said fluid passages of each sinuous path together and with the one common fluid passage disposed adjacent the leading edge, another of said fluid passages being common to both of the sinuous fluid paths and connected to one fluid'passage of each of the sinuous fluid paths by drillings respectively disposed alternately adjacent the root and tip of the blade, said another fluid passage being disposed on an opposite side of the first fluid conduit with respect to the one fluid passage adjacent the leading edge and having an outlet for the blade cooling fluid at one end thereof; and a second fluid conduit formed in the interior or" said blade and extending from the root to the tip thereof and having an inlet at one end thereof through which the blade cooling fluid is introduced therein; a second sinuous fluid passageway formed in said blade and extending completely around the second fluid conduit, said second sinuous passageway comprising a plurality of spaced fluid passages each extending substantially front the root to the tip of the blade, said second plurality of spaced fluid passages defining a second pair of sinuous paths with one path of the second pair being disposed adjacent the upstream side of the blade and the other path of the second pair being disposed adjacent the downstream side of the blade with one of the saidplurality of fluid passages being common to both sinuous paths of the second pair and disposed adjacent the trailing edge of the blade; said one fluid passage of the second pair of fluid passages being disposed adjacent the trailing edge communicating with said second conduit by a drilling disposed adjacent the mid height of the blade and forming a jet through which blade cooling fluid passes from the sec ond fluid conduit into the one fluid passage and cools the trailing edge of the blade from the mid height outwardly toward the root and tip respectively, drillings in said blade alternately arranged adjacent to the root and tip of the blade and connecting the plurality of fluid passages of the pair of paths of said second sinuous passageway together with the one fluid passage disposed adjacent the trailing edge; and another of the said plurality of fluid passages of said seond sinuous passageway being common to both the sinuous fluid paths and connected thereto by drillings respectively disposed alternately adjacent the root and tip of the blade, said fluid passage of another of the said plurality of fluid passages being disposed on an opposite side of the second fluid conduit with respect to the one fluid passage adjacent the trailing edge and having an outlet for blade cooling fluid at one end thereof.
References Cited by the Examiner UNITED STATES PATENTS 2,256,393 9/41 Klein 253-39.15 2,514,105 7/50 Thomas 253-39.15 2,556,736 6/51 Palmatier 253-39.15 2,699,598 1/55 Daugherty.
2,920,866 1/60 Spurrier 253-39.15 2,923,525 2/60 I Creek 25339.15 2,991,973 7/61 Cole 253-39.15 3,032,314 5/62 David 253-39.15 3,051,438 8/62 Roberts 25339.15 3,094,310 6/63 Bowmer 25339.15 3,111,302 11/63 Bowmer 253-3915 JULIUS E. WEST, Primary Examiner.
JOSEPH H. BRANSON, JR., Examiner.

Claims (1)

1. A BLADE ADAPTED FOR USE IN A FLUID FLOW MACHINE SAID BLADE HAVING A ROOT AND A TIP, TWO FLUID CONDUITS FORMED IN SAID BLADE AND EXTENDING FROM SUBSTANTIALLY THE ROOT TO THE TIP THEREOF, AN INLET TO EACH SAID FLUID CONDUIT, THROUGH WHICH A BLADE COOLING FLUID MAY BE INTRODUCED INTO SAID FLUID CONDUITS, TWO SINUOUS FLUID PASSAGEWAY FORMED IN SAID BLADE, EACH OF SAID SINUOUS FLUID PASSAGEWAY COMPRISING A SERIES OF SPACED FLUID PASSAGES WHICH ALSO EXTEND SUBSTANTIALLY FROM THE ROOT TO THE TIP OF THE BLADE, FLUID PATHS WHICH ARE ALTERNATELY ARRANGED ADJACENT TO THE ROOT AND TIP OF THE BLADE, CONNECTING SAID FLUID PASSAGES TOGETHER, ONE FLUID PASSAGE OF EACH SINUOUS FLUID PASSAGEWAY BEING DISPOSED ADJACENT THE LEADING AND TRAILING EDGES OF THE BLADE RESPECTIVELY AND COMMUNICATING WITH THEIR RESPECTIVE FLUID CONDUITS BY WAY OF DRILLINGS DISPOSED ADJACENT THE MID-HEIGHT OF THE BLADE, BLADE COOLING FLUID PASSING THROUGH SAID DRILLING FORMING JETS WHICH COOL THE SAID LEADING AND TRAILING EDGES ADJACENT THE MIDHEIGHTS OF THE BLADE, ONE FLUID PASSAGE OF EACH SINUOUS FLUID PASSAGEWAY BEING PROVIDED WITH AN OUTLET THROUGH WHICH BLADE COOLING FLUID MAY PASS OUT OF THE BLADE, EACH
US258445A 1961-05-02 1963-02-14 Blades for fluid flow machines Expired - Lifetime US3191908A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US258445A US3191908A (en) 1961-05-02 1963-02-14 Blades for fluid flow machines

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1592561A GB950355A (en) 1961-05-02 1961-05-02 Blades for fluid flow machines
US258445A US3191908A (en) 1961-05-02 1963-02-14 Blades for fluid flow machines

Publications (1)

Publication Number Publication Date
US3191908A true US3191908A (en) 1965-06-29

Family

ID=26251641

Family Applications (1)

Application Number Title Priority Date Filing Date
US258445A Expired - Lifetime US3191908A (en) 1961-05-02 1963-02-14 Blades for fluid flow machines

Country Status (1)

Country Link
US (1) US3191908A (en)

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3388888A (en) * 1966-09-14 1968-06-18 Gen Electric Cooled turbine nozzle for high temperature turbine
US4056332A (en) * 1975-05-16 1977-11-01 Bbc Brown Boveri & Company Limited Cooled turbine blade
US4179240A (en) * 1977-08-29 1979-12-18 Westinghouse Electric Corp. Cooled turbine blade
US4456428A (en) * 1979-10-26 1984-06-26 S.N.E.C.M.A. Apparatus for cooling turbine blades
US5156526A (en) * 1990-12-18 1992-10-20 General Electric Company Rotation enhanced rotor blade cooling using a single row of coolant passageways
FR2678318A1 (en) * 1991-06-25 1992-12-31 Snecma COOLED VANE OF TURBINE DISTRIBUTOR.
US5193980A (en) * 1991-02-06 1993-03-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Hollow turbine blade with internal cooling system
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
US5660524A (en) * 1992-07-13 1997-08-26 General Electric Company Airfoil blade having a serpentine cooling circuit and impingement cooling
US5690472A (en) * 1992-02-03 1997-11-25 General Electric Company Internal cooling of turbine airfoil wall using mesh cooling hole arrangement
WO1998045577A1 (en) * 1997-04-07 1998-10-15 Siemens Aktiengesellschaft Method for cooling a turbine blade
US6705836B2 (en) * 2001-08-28 2004-03-16 Snecma Moteurs Gas turbine blade cooling circuits
US20060222494A1 (en) * 2005-03-29 2006-10-05 Siemens Westinghouse Power Corporation Turbine blade leading edge cooling system
US20070104576A1 (en) * 2005-11-08 2007-05-10 United Technologies Corporation Peripheral microcircuit serpentine cooling for turbine airfoils
US20080273963A1 (en) * 2007-02-16 2008-11-06 United Technologies Corporation Impingement skin core cooling for gas turbine engine blade
US20090185903A1 (en) * 2006-04-21 2009-07-23 Beeck Alexander R Turbine Blade
US20090208343A1 (en) * 2006-07-28 2009-08-20 United Technologies Corporation Serpentine microcircuits for hot gas migration
US20090252603A1 (en) * 2008-04-03 2009-10-08 General Electric Company Airfoil for nozzle and a method of forming the machined contoured passage therein
US7690894B1 (en) * 2006-09-25 2010-04-06 Florida Turbine Technologies, Inc. Ceramic core assembly for serpentine flow circuit in a turbine blade
US20100226788A1 (en) * 2009-03-04 2010-09-09 Siemens Energy, Inc. Turbine blade with incremental serpentine cooling channels beneath a thermal skin
US8292582B1 (en) * 2009-07-09 2012-10-23 Florida Turbine Technologies, Inc. Turbine blade with serpentine flow cooling
EP2434093A3 (en) * 2010-09-23 2013-08-07 Rolls-Royce Deutschland Ltd & Co KG Cooled turbine blades for a gas turbine engine
US20150004001A1 (en) * 2012-03-22 2015-01-01 Alstom Technology Ltd Turbine blade
US20160326884A1 (en) * 2015-05-08 2016-11-10 United Technologies Corporation Axial skin core cooling passage for a turbine engine component
US20170175548A1 (en) * 2015-12-21 2017-06-22 General Electric Company Cooling circuits for a multi-wall blade
US10030526B2 (en) 2015-12-21 2018-07-24 General Electric Company Platform core feed for a multi-wall blade
US10119405B2 (en) 2015-12-21 2018-11-06 General Electric Company Cooling circuit for a multi-wall blade
US10221696B2 (en) * 2016-08-18 2019-03-05 General Electric Company Cooling circuit for a multi-wall blade
US10267162B2 (en) 2016-08-18 2019-04-23 General Electric Company Platform core feed for a multi-wall blade
US10364685B2 (en) * 2016-08-12 2019-07-30 Gneral Electric Company Impingement system for an airfoil
US10408062B2 (en) * 2016-08-12 2019-09-10 General Electric Company Impingement system for an airfoil
US10436048B2 (en) * 2016-08-12 2019-10-08 General Electric Comapny Systems for removing heat from turbine components
US10443397B2 (en) * 2016-08-12 2019-10-15 General Electric Company Impingement system for an airfoil
US20190338652A1 (en) * 2018-05-02 2019-11-07 United Technologies Corporation Airfoil having improved cooling scheme
US10830058B2 (en) 2016-11-30 2020-11-10 Rolls-Royce Corporation Turbine engine components with cooling features
US20210148235A1 (en) * 2019-11-14 2021-05-20 United Technologies Corporation Airfoil with connecting rib
US11143039B2 (en) 2015-05-08 2021-10-12 Raytheon Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2256393A (en) * 1937-07-05 1941-09-16 Messerschmitt Boelkow Blohm Cooling the charge of internal combustion engines
US2514105A (en) * 1945-12-07 1950-07-04 Thomas Wilfred Airfoil conditioning means
US2556736A (en) * 1945-06-22 1951-06-12 Curtiss Wright Corp Deicing system for aircraft
US2699598A (en) * 1952-02-08 1955-01-18 Utica Drop Forge & Tool Corp Method of making turbine blades
US2920866A (en) * 1954-12-20 1960-01-12 A V Roe Canada Ltd Hollow air cooled sheet metal turbine blade
US2923525A (en) * 1958-04-04 1960-02-02 Orenda Engines Ltd Hollow gas turbine blade
US2991973A (en) * 1954-10-18 1961-07-11 Parsons & Marine Eng Turbine Cooling of bodies subject to a hot gas stream
US3032314A (en) * 1957-05-28 1962-05-01 Snecma Method of and device for cooling the component elements of machines
US3051438A (en) * 1957-02-22 1962-08-28 Rolls Royce Axial-flow blading with internal fluid passages
US3094310A (en) * 1959-12-09 1963-06-18 Rolls Royce Blades for fluid flow machines
US3111302A (en) * 1960-01-05 1963-11-19 Rolls Royce Blades for fluid flow machines

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2256393A (en) * 1937-07-05 1941-09-16 Messerschmitt Boelkow Blohm Cooling the charge of internal combustion engines
US2556736A (en) * 1945-06-22 1951-06-12 Curtiss Wright Corp Deicing system for aircraft
US2514105A (en) * 1945-12-07 1950-07-04 Thomas Wilfred Airfoil conditioning means
US2699598A (en) * 1952-02-08 1955-01-18 Utica Drop Forge & Tool Corp Method of making turbine blades
US2991973A (en) * 1954-10-18 1961-07-11 Parsons & Marine Eng Turbine Cooling of bodies subject to a hot gas stream
US2920866A (en) * 1954-12-20 1960-01-12 A V Roe Canada Ltd Hollow air cooled sheet metal turbine blade
US3051438A (en) * 1957-02-22 1962-08-28 Rolls Royce Axial-flow blading with internal fluid passages
US3032314A (en) * 1957-05-28 1962-05-01 Snecma Method of and device for cooling the component elements of machines
US2923525A (en) * 1958-04-04 1960-02-02 Orenda Engines Ltd Hollow gas turbine blade
US3094310A (en) * 1959-12-09 1963-06-18 Rolls Royce Blades for fluid flow machines
US3111302A (en) * 1960-01-05 1963-11-19 Rolls Royce Blades for fluid flow machines

Cited By (56)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3388888A (en) * 1966-09-14 1968-06-18 Gen Electric Cooled turbine nozzle for high temperature turbine
US4056332A (en) * 1975-05-16 1977-11-01 Bbc Brown Boveri & Company Limited Cooled turbine blade
US4179240A (en) * 1977-08-29 1979-12-18 Westinghouse Electric Corp. Cooled turbine blade
US4456428A (en) * 1979-10-26 1984-06-26 S.N.E.C.M.A. Apparatus for cooling turbine blades
US5156526A (en) * 1990-12-18 1992-10-20 General Electric Company Rotation enhanced rotor blade cooling using a single row of coolant passageways
US5193980A (en) * 1991-02-06 1993-03-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Hollow turbine blade with internal cooling system
US5215431A (en) * 1991-06-25 1993-06-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Cooled turbine guide vane
FR2678318A1 (en) * 1991-06-25 1992-12-31 Snecma COOLED VANE OF TURBINE DISTRIBUTOR.
US5690472A (en) * 1992-02-03 1997-11-25 General Electric Company Internal cooling of turbine airfoil wall using mesh cooling hole arrangement
US5660524A (en) * 1992-07-13 1997-08-26 General Electric Company Airfoil blade having a serpentine cooling circuit and impingement cooling
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
WO1998045577A1 (en) * 1997-04-07 1998-10-15 Siemens Aktiengesellschaft Method for cooling a turbine blade
US6705836B2 (en) * 2001-08-28 2004-03-16 Snecma Moteurs Gas turbine blade cooling circuits
US7416390B2 (en) * 2005-03-29 2008-08-26 Siemens Power Generation, Inc. Turbine blade leading edge cooling system
US20060222494A1 (en) * 2005-03-29 2006-10-05 Siemens Westinghouse Power Corporation Turbine blade leading edge cooling system
US8220522B2 (en) 2005-11-08 2012-07-17 United Technologies Corporation Peripheral microcircuit serpentine cooling for turbine airfoils
US20070104576A1 (en) * 2005-11-08 2007-05-10 United Technologies Corporation Peripheral microcircuit serpentine cooling for turbine airfoils
US8215374B2 (en) 2005-11-08 2012-07-10 United Technologies Corporation Peripheral microcircuit serpentine cooling for turbine airfoils
US20100221098A1 (en) * 2005-11-08 2010-09-02 United Technologies Corporation Peripheral Microcircuit Serpentine Cooling for Turbine Airfoils
US7744347B2 (en) * 2005-11-08 2010-06-29 United Technologies Corporation Peripheral microcircuit serpentine cooling for turbine airfoils
US8092175B2 (en) * 2006-04-21 2012-01-10 Siemens Aktiengesellschaft Turbine blade
US20090185903A1 (en) * 2006-04-21 2009-07-23 Beeck Alexander R Turbine Blade
US7581928B1 (en) * 2006-07-28 2009-09-01 United Technologies Corporation Serpentine microcircuits for hot gas migration
US20090208343A1 (en) * 2006-07-28 2009-08-20 United Technologies Corporation Serpentine microcircuits for hot gas migration
US7690894B1 (en) * 2006-09-25 2010-04-06 Florida Turbine Technologies, Inc. Ceramic core assembly for serpentine flow circuit in a turbine blade
US7837441B2 (en) * 2007-02-16 2010-11-23 United Technologies Corporation Impingement skin core cooling for gas turbine engine blade
US20080273963A1 (en) * 2007-02-16 2008-11-06 United Technologies Corporation Impingement skin core cooling for gas turbine engine blade
US8246306B2 (en) * 2008-04-03 2012-08-21 General Electric Company Airfoil for nozzle and a method of forming the machined contoured passage therein
US20090252603A1 (en) * 2008-04-03 2009-10-08 General Electric Company Airfoil for nozzle and a method of forming the machined contoured passage therein
US8721285B2 (en) * 2009-03-04 2014-05-13 Siemens Energy, Inc. Turbine blade with incremental serpentine cooling channels beneath a thermal skin
US20100226788A1 (en) * 2009-03-04 2010-09-09 Siemens Energy, Inc. Turbine blade with incremental serpentine cooling channels beneath a thermal skin
US8292582B1 (en) * 2009-07-09 2012-10-23 Florida Turbine Technologies, Inc. Turbine blade with serpentine flow cooling
EP2434093A3 (en) * 2010-09-23 2013-08-07 Rolls-Royce Deutschland Ltd & Co KG Cooled turbine blades for a gas turbine engine
US9051841B2 (en) 2010-09-23 2015-06-09 Rolls-Royce Deutschland Ltd & Co Kg Cooled turbine blades for a gas-turbine engine
US20150004001A1 (en) * 2012-03-22 2015-01-01 Alstom Technology Ltd Turbine blade
EP2828484B1 (en) * 2012-03-22 2019-05-08 Ansaldo Energia IP UK Limited Turbine blade
US9932836B2 (en) * 2012-03-22 2018-04-03 Ansaldo Energia Ip Uk Limited Turbine blade
US20160326884A1 (en) * 2015-05-08 2016-11-10 United Technologies Corporation Axial skin core cooling passage for a turbine engine component
US11143039B2 (en) 2015-05-08 2021-10-12 Raytheon Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10323524B2 (en) * 2015-05-08 2019-06-18 United Technologies Corporation Axial skin core cooling passage for a turbine engine component
US20170175548A1 (en) * 2015-12-21 2017-06-22 General Electric Company Cooling circuits for a multi-wall blade
US10781698B2 (en) 2015-12-21 2020-09-22 General Electric Company Cooling circuits for a multi-wall blade
US10030526B2 (en) 2015-12-21 2018-07-24 General Electric Company Platform core feed for a multi-wall blade
US10119405B2 (en) 2015-12-21 2018-11-06 General Electric Company Cooling circuit for a multi-wall blade
US10060269B2 (en) * 2015-12-21 2018-08-28 General Electric Company Cooling circuits for a multi-wall blade
US10436048B2 (en) * 2016-08-12 2019-10-08 General Electric Comapny Systems for removing heat from turbine components
US10408062B2 (en) * 2016-08-12 2019-09-10 General Electric Company Impingement system for an airfoil
US10443397B2 (en) * 2016-08-12 2019-10-15 General Electric Company Impingement system for an airfoil
US10364685B2 (en) * 2016-08-12 2019-07-30 Gneral Electric Company Impingement system for an airfoil
US10221696B2 (en) * 2016-08-18 2019-03-05 General Electric Company Cooling circuit for a multi-wall blade
US10267162B2 (en) 2016-08-18 2019-04-23 General Electric Company Platform core feed for a multi-wall blade
US10830058B2 (en) 2016-11-30 2020-11-10 Rolls-Royce Corporation Turbine engine components with cooling features
US20190338652A1 (en) * 2018-05-02 2019-11-07 United Technologies Corporation Airfoil having improved cooling scheme
US10753210B2 (en) * 2018-05-02 2020-08-25 Raytheon Technologies Corporation Airfoil having improved cooling scheme
US20210148235A1 (en) * 2019-11-14 2021-05-20 United Technologies Corporation Airfoil with connecting rib
US11952911B2 (en) * 2019-11-14 2024-04-09 Rtx Corporation Airfoil with connecting rib

Similar Documents

Publication Publication Date Title
US3191908A (en) Blades for fluid flow machines
US3045965A (en) Turbine blades, vanes and the like
US6210111B1 (en) Turbine blade with platform cooling
US3094310A (en) Blades for fluid flow machines
US3635586A (en) Method and apparatus for turbine blade cooling
DE102007007177B4 (en) Method and apparatus for cooling gas turbine rotor blades
JP4510864B2 (en) Turbine blade with coolant passage in turbine
US3782852A (en) Gas turbine engine blades
US4127358A (en) Blade or vane for a gas turbine engine
US20170234154A1 (en) Turbine stator vane with closed-loop sequential impingement cooling insert
EP3196415B1 (en) Cooled turbine vane
US3809494A (en) Vane or blade for a gas turbine engine
US9388699B2 (en) Crossover cooled airfoil trailing edge
US3111302A (en) Blades for fluid flow machines
US10830061B2 (en) Turbine airfoil with internal cooling channels having flow splitter feature
US20160209035A1 (en) Combustion hole insert with integrated film restarter
EP3428398A1 (en) Airfoil and corresponding method of cooling a tip rail
JPH09203301A (en) Steam cooled blade
CN110300838A (en) Heat structure for outer diameter mount type turbo blade
JP2015521706A (en) Turbine airfoil with cast platform cooling circuit
JP2003106169A (en) Gas turbine and method for operating the same
CN207526530U (en) A kind of efficient cooling blade of gas-turbine unit
US10519782B2 (en) Airfoil having serpentine core resupply flow control
US3427001A (en) Aerofoil shaped blade
US3422623A (en) Jet engines with cooling means