US2801072A - Hollow blade for fluid flow operated machine - Google Patents

Hollow blade for fluid flow operated machine Download PDF

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Publication number
US2801072A
US2801072A US224325A US22432551A US2801072A US 2801072 A US2801072 A US 2801072A US 224325 A US224325 A US 224325A US 22432551 A US22432551 A US 22432551A US 2801072 A US2801072 A US 2801072A
Authority
US
United States
Prior art keywords
blade
fluid flow
operated machine
flow operated
root
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
US224325A
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English (en)
Inventor
Rosskopf Hans
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.)
Individual
Original Assignee
Individual
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 to FR511A priority Critical patent/FR1262551A/fr
Application filed by Individual filed Critical Individual
Priority to US224325A priority patent/US2801072A/en
Priority to CH325966D priority patent/CH325966A/fr
Priority to GB14531/51A priority patent/GB737167A/en
Priority to GB14530/51A priority patent/GB737166A/en
Priority to DEO1673A priority patent/DE938280C/de
Priority to DEO1674A priority patent/DE938691C/de
Priority to BE504383D priority patent/BE504383A/xx
Application granted granted Critical
Publication of US2801072A publication Critical patent/US2801072A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Hollow blades manufactured from stamped metal sheets without any bead and welding have also been proposed. Such blades are secured in the blade holder or disk by means of pins fitted in two grooves provided approximately in axial direction in faces of the blade root. With cooled blades, the grooves further provide a passage of cooling fluid through a portion thereof, but a con siderable amount of cooling fluid is thus lost. Such a leakage is not much reduced by the overlap provided for successive blades.
  • a further object is to provide as improved blade and blade-holder combination whereby a fluid-tight assembly is obtained with blades arranged for inner cooling.
  • I provide an improved hollow blade for fluid flow operated machines, particularly gas turbine, wherein a tubular portion having a wall which tapers to the blade tip starts integrally from a thick, blade root block preferably of the Laval type.
  • Fig. 1 is a front elevation of my improved blade, the lower part being shown in section.
  • Fig. 2 is a cross-section taken along line 2-2 on Fig. 1.
  • Fig. 3 is a view similar to Fig. 1, showing a modified blade, arranged for inner cooling.
  • Fig. 4 is a longitudinal cross-section taken along line 4-4 of Fig. 3.
  • Fig. 5 is a longitudinal section of a modified type of blade, with a cooling jacket.
  • Fig. 6 is a cross-section taken along line 6-6 on Fig. 5.
  • Fig. 7 is a longitudinal section taken along line 7-7 on Fig. 5.
  • my blade comprises a solid, root block 1, preferably of the Laval type, and an integral tubular portion 2 produced from a blank of material, preferably an austenitic alloy.
  • the production is effected in one process combining a deep stamping with a diepressing; through the deep stamping step, the starting blank is converted into an upper sleeve portion having a wall of upwardly decreasing thickness, and an integral, lower portion which is a solid body; upon pressing in a suitable die, the sleeve portion is shaped to the desired cross-section and the solid body portion to a solid root block having opposed semi-cylindrical surfaces.
  • Fig. 2 illustrates the shape of portion 2 in cross-section and the relative position of said portion with respect to the root block. The front face of the root block on the right side of Fig. 2 is partly hidden by the trailing edge of portion 2.
  • passages are provided through the root'block 1 for ingress of cooling fluid, preferably air. It is preferred to have a pair of bores 3, 4 in substantial alignment with the leading or upstream edge of portion 2 and the trailing or downstream edge respectively; bores 3 and 4 are preferably slanting towards the corresponding blade edges so that the inner wall of said edges can etficiently be swept by cooling air. Bores 3 and 4 have different diameters. The bigger bore 3 is adjacent to the leading edge which is generally hotter while the smaller bore 4 is adjacent to the less hot, trailing edge. Consequently it will be understood that provision is made for a suitable distribution of cooling air streams.
  • a middle recess 5 is formed in the lower end of root block 1 to provide for supply of cooling air to both bores 3 and 4.
  • the recess does not extend to the marginal portions of the end of root block 1, leaving the same unaltered so that fluid-tightness is preserved where the blade contacts the blade holder.
  • a passage 6 is provided between bores 3, 4 and has a cross-section (Fig. 4) which may taper towards the blade tip.
  • an air guiding and distributing device generally denoted by reference character 7 is arranged within the blade, to cause cooling air from passages 3 and 4 to flow and impinge along the inner surface of the tubular blade portion.
  • The-device 7 has a foot portion 8 disposed in passage 6a and held therein by wedges 9, 10 which are welded to the foot portion 8 and root block 1 as at 11, 12 after being set in passage 6a. It will thus be seen that the weld beads, located in recess 5, do not project from the root block.
  • the device 7 may be produced from sheet metal cut to the required form and doubled back along folding line 13 to provide a tubular sleeve portion in its middle and upper part and a twoply portion in its lower part or foot portion 8, opposite edges of the original sheet being assembled together along line 14 as shown; the assembly is suitably curved to have a substantially aerofoil cross-section approximating that of tubular blade portion 2 as shown.
  • the sheet metal is preferably formed with longitudinal corrugations 15 having such a relief as to come into contact with the inner surface of tubular blade portion 2 as shown in Fig. 6.
  • cooling air stream rising through passages 3, 4 is split into several adjacent separate fiat streamlets that flow over the inner wall of tubular blade portion 2; the cross-sectional area of the air passages as defined between device 7 and blade portion 2, generally diminishes upwards from the outlet side of passages 3 and 4.
  • a hollow blade for a fluid flow operated machine, particularly a gas turbine which is an integral metal unit comprising a solid root portion having a middle recess in its lower end and a tubular portion projecting upwardly from the upper end of said root portion, said tubular portion having an upwardly thinning, tapering wall and an aerofoil cross-section so as to have a leading edge and a trailing edge, said root portion further having a couple of bores extending from said middle recess to the inner space enclosed by said tubular portion, said bores being slanted,

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US224325A 1949-11-22 1951-05-03 Hollow blade for fluid flow operated machine Expired - Lifetime US2801072A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
FR511A FR1262551A (fr) 1949-11-22 1949-11-22 Aube creuse pour machines à écoulement de fluide
US224325A US2801072A (en) 1949-11-22 1951-05-03 Hollow blade for fluid flow operated machine
CH325966D CH325966A (fr) 1949-11-22 1951-06-12 Aube pour turbo-machine
GB14530/51A GB737166A (en) 1949-11-22 1951-06-19 Improvements in or relating to fluid-cooled hollow turbine or like blades
GB14531/51A GB737167A (en) 1949-11-22 1951-06-19 Improvements in hollow blades for fluid-flow operated machines
DEO1673A DE938280C (de) 1949-11-22 1951-06-24 Hohlschaufel fuer Stroemungsmaschinen
DEO1674A DE938691C (de) 1949-11-22 1951-06-24 Aufbau und Befestigung von Einsaetzen fuer die Kuehlmittelfuehrung innengekuehlter Hohlschaufeln fuer Stroemungsmaschinen
BE504383D BE504383A (de) 1949-11-22 1951-06-30

Applications Claiming Priority (7)

Application Number Priority Date Filing Date Title
FR511A FR1262551A (fr) 1949-11-22 1949-11-22 Aube creuse pour machines à écoulement de fluide
US224325A US2801072A (en) 1949-11-22 1951-05-03 Hollow blade for fluid flow operated machine
CH325966T 1951-06-12
GB14530/51A GB737166A (en) 1949-11-22 1951-06-19 Improvements in or relating to fluid-cooled hollow turbine or like blades
DEO1673A DE938280C (de) 1949-11-22 1951-06-24 Hohlschaufel fuer Stroemungsmaschinen
DEO1674A DE938691C (de) 1949-11-22 1951-06-24 Aufbau und Befestigung von Einsaetzen fuer die Kuehlmittelfuehrung innengekuehlter Hohlschaufeln fuer Stroemungsmaschinen
BE504383T 1951-06-30

Publications (1)

Publication Number Publication Date
US2801072A true US2801072A (en) 1957-07-30

Family

ID=10042863

Family Applications (1)

Application Number Title Priority Date Filing Date
US224325A Expired - Lifetime US2801072A (en) 1949-11-22 1951-05-03 Hollow blade for fluid flow operated machine

Country Status (6)

Country Link
US (1) US2801072A (de)
BE (1) BE504383A (de)
CH (1) CH325966A (de)
DE (2) DE938691C (de)
FR (1) FR1262551A (de)
GB (2) GB737166A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3087484A1 (fr) * 2018-10-18 2020-04-24 Safran Aircraft Engines Aube de turbomachine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2121483B (en) * 1982-06-08 1985-02-13 Rolls Royce Cooled turbine blade for a gas turbine engine
US4582467A (en) * 1983-12-22 1986-04-15 United Technologies Corporation Two stage rotor assembly with improved coolant flow

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2013622A (en) * 1932-03-24 1935-09-03 Parsons C A & Co Ltd Method of making turbine blades
FR880656A (fr) * 1940-09-20 1943-04-01 Bmw Flugmotorenbau Gmbh Rotor pour turbines à gaz d'échappement
CH237453A (de) * 1942-02-04 1945-04-30 Bmw Flugmotorenbau Ges Mbh Innengekühlte Turbinenschaufel.
GB584580A (en) * 1943-12-28 1947-01-17 Masch Fabrick Oerlikon Improvements in or relating to turbine blades
FR949459A (fr) * 1947-07-09 1949-08-31 Aubes pour rotors
FR981599A (fr) * 1948-12-31 1951-05-28 Dispositif amortisseur de vibrations
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
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE494165C (de) * 1927-11-17 1930-03-19 Charles Algernon Parsons Verfahren zur Herstellung von Turbinenschaufeln mit Fuss- und Schaftteil durch Walzen aus einem Rohwerkstueck
DE604732C (de) * 1932-03-24 1934-10-29 Parsons C A & Co Ltd Verfahren zur Herstellung von hohlen, nahtlosen Turbinenschaufeln
DE625799C (de) * 1934-04-25 1936-02-15 Parsons C A & Co Ltd Verfahren zur Herstellung hohler Turbinenschaufeln durch Ausstrecken eines gefuellten Hohlwerkstuecks von einer zur Laenge der fertigen Schaufel relativ geringen Laenge

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2013622A (en) * 1932-03-24 1935-09-03 Parsons C A & Co Ltd Method of making turbine blades
FR880656A (fr) * 1940-09-20 1943-04-01 Bmw Flugmotorenbau Gmbh Rotor pour turbines à gaz d'échappement
CH237453A (de) * 1942-02-04 1945-04-30 Bmw Flugmotorenbau Ges Mbh Innengekühlte Turbinenschaufel.
US2563269A (en) * 1943-05-22 1951-08-07 Lockheed Aircraft Corp Gas turbine
GB584580A (en) * 1943-12-28 1947-01-17 Masch Fabrick Oerlikon Improvements in or relating to turbine blades
FR949459A (fr) * 1947-07-09 1949-08-31 Aubes pour rotors
US2559131A (en) * 1948-04-22 1951-07-03 Oestrich Hollow blade for gas turbines and the like
FR981599A (fr) * 1948-12-31 1951-05-28 Dispositif amortisseur de vibrations
US2648520A (en) * 1949-08-02 1953-08-11 Heinz E Schmitt Air-cooled turbine blade

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3087484A1 (fr) * 2018-10-18 2020-04-24 Safran Aircraft Engines Aube de turbomachine

Also Published As

Publication number Publication date
FR1262551A (fr) 1961-06-05
GB737166A (en) 1955-09-21
BE504383A (de) 1951-12-31
GB737167A (en) 1955-09-21
DE938280C (de) 1956-01-26
DE938691C (de) 1956-02-02
CH325966A (fr) 1957-11-30

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