US2925996A - Blades for compressors and turbines - Google Patents

Blades for compressors and turbines Download PDF

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Publication number
US2925996A
US2925996A US489945A US48994555A US2925996A US 2925996 A US2925996 A US 2925996A US 489945 A US489945 A US 489945A US 48994555 A US48994555 A US 48994555A US 2925996 A US2925996 A US 2925996A
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Prior art keywords
blade
flange means
blades
walls
compressors
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US489945A
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Edward A Stalker
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Stalker Corp
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Stalker Corp
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Priority to US489945A priority Critical patent/US2925996A/en
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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
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration

Definitions

  • This invention relates to hollow blades, particularly sheet metal blades, for compressors and turbines.
  • An object of the invention is to provide a structure for the blades which is light and strong.
  • Another object is to provide a sheet metal blade having light and strong internal structure for supporting the blade walls.
  • Fig. 1 is a side elevation of a blade according to this invention
  • Fig. 2 is a section on line 22 in Fig. 1;
  • Fig. 3 is a fragmentary enlarged view of the convex side of the blade of Fig. 1;
  • Fig. 4 is a fragmentary section on line 4-4 in Fig. 3;
  • Fig. 5 is a fragmentary section on line 5-5 in Fig. 3;
  • Fig. 6 is a section on line 6-6 in Fig. 3;
  • Fig. 7 is a fragmentary section on line 7-7 in Fig. 2.
  • Compressor or turbine blades to be light in weight employ thin walls enclosing hollow interiors.
  • the walls tend to vibrate locally often to the extent that they develop fatigue cracks and disintegrate.
  • This invention provides means of supporting the walls at relatively close intervals to exclude these local vibrations.
  • the supporting means also greatly increases the strength of the blade to bending and twisting actions.
  • the blade is indicated generally as 10, Figs. 1 and 2, comprising the upper or convex wall 12, the lower or partially concave wall 14, base 16 and internal structural means 18.
  • the upper and lower walls are juxtaposed in spaced relation defining the hollow interior 20. They are supported one on the other at the leading and trailing edges 22 and 24 respectively and fixed together at these edges.
  • the blade walls and the internal structural means 18 are fixed in an opening 30 in the base 16.
  • the internal structural means comprises one or more beaded or indented beams extending along a major extent of the blade span which is the dimension extending outward from the base 16.
  • the front and rear beams 40 and 42 respectively extend preferably along the whole span.
  • the front beam has the upper flange means '44 and the lower flange means 46 each integral with the vertical front and rear webs 5'4 and 48, and faying the inner surfaces of upper and lower walls 12 and 14, respectively.
  • Each upper flange means has the beads 50 (Fig. 3) each with its major dimension of length preferably directed at a substantial angle to the chord direction which is perpendicular to the direction of the span. Preferably some heads 52 have their major direction at a substantial angle to the beads 50 or parallel to the chord direction.
  • the front vertical portion of the beam at the junction of the upper and lower flange means constitutes a vertical front web 54.
  • the diagonal beads 50 form with this front web 54 and rear web 48 a truss or system which 2,925,996 Patented Feb. 23, 1960 2'. can sustain loads normal: to the span and parallel to the chord direction.
  • a V-shap'e'd stiffener or shock absorbing element 55" is located in the hollow nose portion of the blade forwardly of web 54 and is bonded to the upper and lower blade walls" by fused metal.
  • the structure is very strong in bending and torsion.
  • Each diagonal bead 50 is indented inwardly. That is it extends in depth inwardly of theblade interior preferably into contact with the lower flange means as shown in Figs. 2, 5 and 6 and isflkedther'etb by fused metal.
  • the beads- 52, Fig. 4 preferably extend in depthinwardly for only' a short distance and do not reach the lower flange means.
  • the beads 50 and 52 divide the surface areas of the blade walls into small increments of area such as 60 in Fig. 3. These are sufliciently small that they will not undergo significant vibration when the blade is being rotated in use.
  • the rear beam means 42 is similar to the front one. It includes a vertical front web 71, the upper flange means 72 and the lower flange means 74 lapped and joined at 76, preferaby by fused metal.
  • the upper flange means has the diagonal beads and the chordwise beads 82.
  • the diagonal beads 80 extend in depth inward similarly to beads 50 as shown particularly in Fig. 5.
  • the flange means fay the inner surfaces of the adjacent walls of the blade, either upper or lower wall, and are fixed to the respective adjacent wall by fused metal, preferably by high temperature solder.
  • an upper wall and a lower wall juxtaposed and spaced apart along portions thereof defining a hollow interior of said blade, and beam means within said interior comprising fro'nt and rear webs extending along a major portion of the spanwise length of said blade, walls defining upper and lower flange means extending chordwise from one said Web to the other'and spanwise along a major portion of the spanwise lengths of said webs, said upper flange means faying the inner surface of said upper wall, said lower flange means faying the inner surface of said lower wall, at least one of said flange means having a plurality of beads indented inwardly therein, each said bead having its major length 3 a directed at a substantial angle with respect to the chord direction of said blade, each said bead extending inward into contact with the opposite wall of said blade and being fixed thereto, and fused metal means fixing each said flange means to its adjacent wall.
  • each said bead has its length extending from a locality adjacent said front web to a locality adjacent said rear web at a substantial angle with respect to the'spanwis'e direction.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Feb. 23, 1960 E. A. STALKER 6 BLADES FOR COMPRESSORS AND TURBINES Filed Feb. 23, 1955 IN V EN TOR.
Fr g- 5 ML United States Patent BLADES FOR COMPRESSORS TURBINES Edward A. Stalker, Bay City, Mich, assignor to The Stalker Corporation, a corporationof Michigan- Applicati'on February 23, 1955, SeriallNo. 489,945
3 Claims. (Cl. 253-77) This invention relates to hollow blades, particularly sheet metal blades, for compressors and turbines.
An object of the invention is to provide a structure for the blades which is light and strong.
Another object is to provide a sheet metal blade having light and strong internal structure for supporting the blade walls.
Other objects will appear from the description, drawings and claims.
The above objects are accomplished by the means illustrated in the accompanying drawings in which- Fig. 1 is a side elevation of a blade according to this invention;
Fig. 2 is a section on line 22 in Fig. 1;
Fig. 3 is a fragmentary enlarged view of the convex side of the blade of Fig. 1;
Fig. 4 is a fragmentary section on line 4-4 in Fig. 3;
Fig. 5 is a fragmentary section on line 5-5 in Fig. 3;
Fig. 6 is a section on line 6-6 in Fig. 3; and
Fig. 7 is a fragmentary section on line 7-7 in Fig. 2.
Compressor or turbine blades to be light in weight employ thin walls enclosing hollow interiors. The walls tend to vibrate locally often to the extent that they develop fatigue cracks and disintegrate. This invention provides means of supporting the walls at relatively close intervals to exclude these local vibrations. The supporting means also greatly increases the strength of the blade to bending and twisting actions.
Referring now to the drawings, the blade is indicated generally as 10, Figs. 1 and 2, comprising the upper or convex wall 12, the lower or partially concave wall 14, base 16 and internal structural means 18.
The upper and lower walls are juxtaposed in spaced relation defining the hollow interior 20. They are supported one on the other at the leading and trailing edges 22 and 24 respectively and fixed together at these edges.
The blade walls and the internal structural means 18 are fixed in an opening 30 in the base 16.
The internal structural means comprises one or more beaded or indented beams extending along a major extent of the blade span which is the dimension extending outward from the base 16. For instance in Figs. 1, 2, 3 and 6 the front and rear beams 40 and 42 respectively extend preferably along the whole span. The front beam has the upper flange means '44 and the lower flange means 46 each integral with the vertical front and rear webs 5'4 and 48, and faying the inner surfaces of upper and lower walls 12 and 14, respectively.
Each upper flange means has the beads 50 (Fig. 3) each with its major dimension of length preferably directed at a substantial angle to the chord direction which is perpendicular to the direction of the span. Preferably some heads 52 have their major direction at a substantial angle to the beads 50 or parallel to the chord direction.
The front vertical portion of the beam at the junction of the upper and lower flange means constitutes a vertical front web 54. The diagonal beads 50 form with this front web 54 and rear web 48 a truss or system which 2,925,996 Patented Feb. 23, 1960 2'. can sustain loads normal: to the span and parallel to the chord direction. A V-shap'e'd stiffener or shock absorbing element 55" is located in the hollow nose portion of the blade forwardly of web 54 and is bonded to the upper and lower blade walls" by fused metal. Thus the structure is very strong in bending and torsion.
Each diagonal bead 50 is indented inwardly. That is it extends in depth inwardly of theblade interior preferably into contact with the lower flange means as shown in Figs. 2, 5 and 6 and isflkedther'etb by fused metal.
The beads- 52, Fig. 4, preferably extend in depthinwardly for only' a short distance and do not reach the lower flange means.
The beads 50 and 52 divide the surface areas of the blade walls into small increments of area such as 60 in Fig. 3. These are sufliciently small that they will not undergo significant vibration when the blade is being rotated in use.
The rear beam means 42 is similar to the front one. It includes a vertical front web 71, the upper flange means 72 and the lower flange means 74 lapped and joined at 76, preferaby by fused metal. The upper flange means has the diagonal beads and the chordwise beads 82. The diagonal beads 80 extend in depth inward similarly to beads 50 as shown particularly in Fig. 5.
The flange means fay the inner surfaces of the adjacent walls of the blade, either upper or lower wall, and are fixed to the respective adjacent wall by fused metal, preferably by high temperature solder.
It will now be clear that I have disclosed a light structure for a blade, one which provides great strength against bending and twisting and which supports the outer walls of the blades at close intervals excluding significant local vibrations.
While I have illustrated specific forms of the invention, it is to be understood that variations may be made therein and that I intend to claim my invention broadly as indicated by the appended claims.
I claim:
1. In combination in a fluid turning blade for compressors and turbines, an upper wall and a lower wall juxtaposed and spaced apart along portions thereof defining a hollow interior of said blade, and beam means within said interior comprising fro'nt and rear webs extending along a major portion of the spanwise length of said blade, walls defining upper and lower flange means extending chordwise from one said web to the other and spanwise along a major portion of the spanwise lengths of said webs, said upper flange means faying the inner surface of said upper wall, said lower flange means faying the inner surface of said lower wall, at least one of said flange means having a plurality of beads indented inwardly therein, each said bead having its major length directed at a substantial angle with respect to the chord direction of said blade, and fused metal means between each said flange means and the inner wall surface adjacent thereto fixing due to the other.
2. In combination in a fluid turning blade for compressors and turbines, an upper wall and a lower wall juxtaposed and spaced apart along portions thereof defining a hollow interior of said blade, and beam means within said interior comprising fro'nt and rear webs extending along a major portion of the spanwise length of said blade, walls defining upper and lower flange means extending chordwise from one said Web to the other'and spanwise along a major portion of the spanwise lengths of said webs, said upper flange means faying the inner surface of said upper wall, said lower flange means faying the inner surface of said lower wall, at least one of said flange means having a plurality of beads indented inwardly therein, each said bead having its major length 3 a directed at a substantial angle with respect to the chord direction of said blade, each said bead extending inward into contact with the opposite wall of said blade and being fixed thereto, and fused metal means fixing each said flange means to its adjacent wall.
3. The combination as defined in claim 1 in which each said bead has its length extending from a locality adjacent said front web to a locality adjacent said rear web at a substantial angle with respect to the'spanwis'e direction. i 1
References Cited in the file of this patent UNITED STATES PATENTS 2,230,393 Thomson 'Feb. 4, 1941 Pecker Nov. 7, 1944 La Motte Oct. 12, 1948 Bragdon Mar. 22, 1949 FOREIGN PATENTS Great Britain 1913 Great Britain May 28, 1948 Great Britain Feb. 9, 1955 Germany Feb. 22, 1954 Germany Oct. 20, 1952 Germany Dec. 22, 1952 Germany Apr. 27, 1953 Germany Oct. 8. 1953
US489945A 1955-02-23 1955-02-23 Blades for compressors and turbines Expired - Lifetime US2925996A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4558898A (en) * 1984-05-22 1985-12-17 Deaver Dann T Aerodynamic wing device and method of making same
US20050084380A1 (en) * 2003-10-16 2005-04-21 Pratt & Whitney Canada Corp. Hollow turbine blade stiffening
US20130243587A1 (en) * 2010-12-22 2013-09-19 Hiroyuki Yamashita Turbine vane of steam turbine and steam turbine

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191326604A (en) * 1913-11-19 1914-09-10 Selas Lighting Company Ltd Improvements relating to Rotary Pumps or Compressors.
US2230393A (en) * 1937-03-29 1941-02-04 John B Thomson Airplane structural element
US2362301A (en) * 1943-07-17 1944-11-07 Joseph S Pecker Aircraft rotor wing construction
GB602530A (en) * 1945-10-16 1948-05-28 Bristol Aeroplane Co Ltd Improvements in or relating to gas turbines
US2451099A (en) * 1945-08-28 1948-10-12 Gen Motors Corp Method of uniting metal pieces by means of a bonding layer of predetermined thickness
US2465007A (en) * 1944-01-05 1949-03-22 Gen Motors Corp Aircraft propeller
DE852786C (en) * 1943-11-10 1952-10-20 Versuchsanstalt Fuer Luftfahrt Time-graded cooling air throughput through the blades of gas or exhaust gas turbines
DE860438C (en) * 1941-03-28 1952-12-22 Versuchsanstalt Fuer Luftfahrt Hollow blade for gas or exhaust gas turbines
DE872416C (en) * 1943-07-23 1953-04-27 Versuchsanstalt Fuer Luftfahrt Hollow blade turbine with blades folded from sheet metal
DE892698C (en) * 1943-05-21 1953-10-08 Messerschmitt Boelkow Blohm Air-cooled hollow blade, especially for gas and exhaust gas turbines
DE758097C (en) * 1940-06-08 1954-02-22 Versuchsanstalt Fuer Luftfahrt Blade attachment for gas or exhaust turbine blades
GB723392A (en) * 1951-10-10 1955-02-09 Gen Motors Corp Improvements in gas turbine or like blades

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB191326604A (en) * 1913-11-19 1914-09-10 Selas Lighting Company Ltd Improvements relating to Rotary Pumps or Compressors.
US2230393A (en) * 1937-03-29 1941-02-04 John B Thomson Airplane structural element
DE758097C (en) * 1940-06-08 1954-02-22 Versuchsanstalt Fuer Luftfahrt Blade attachment for gas or exhaust turbine blades
DE860438C (en) * 1941-03-28 1952-12-22 Versuchsanstalt Fuer Luftfahrt Hollow blade for gas or exhaust gas turbines
DE892698C (en) * 1943-05-21 1953-10-08 Messerschmitt Boelkow Blohm Air-cooled hollow blade, especially for gas and exhaust gas turbines
US2362301A (en) * 1943-07-17 1944-11-07 Joseph S Pecker Aircraft rotor wing construction
DE872416C (en) * 1943-07-23 1953-04-27 Versuchsanstalt Fuer Luftfahrt Hollow blade turbine with blades folded from sheet metal
DE852786C (en) * 1943-11-10 1952-10-20 Versuchsanstalt Fuer Luftfahrt Time-graded cooling air throughput through the blades of gas or exhaust gas turbines
US2465007A (en) * 1944-01-05 1949-03-22 Gen Motors Corp Aircraft propeller
US2451099A (en) * 1945-08-28 1948-10-12 Gen Motors Corp Method of uniting metal pieces by means of a bonding layer of predetermined thickness
GB602530A (en) * 1945-10-16 1948-05-28 Bristol Aeroplane Co Ltd Improvements in or relating to gas turbines
GB723392A (en) * 1951-10-10 1955-02-09 Gen Motors Corp Improvements in gas turbine or like blades

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4558898A (en) * 1984-05-22 1985-12-17 Deaver Dann T Aerodynamic wing device and method of making same
US20050084380A1 (en) * 2003-10-16 2005-04-21 Pratt & Whitney Canada Corp. Hollow turbine blade stiffening
WO2005035947A1 (en) * 2003-10-16 2005-04-21 Pratt & Whitney Canada Corp. Hollow turbine blade stiffening
US7001150B2 (en) 2003-10-16 2006-02-21 Pratt & Whitney Canada Corp. Hollow turbine blade stiffening
US20130243587A1 (en) * 2010-12-22 2013-09-19 Hiroyuki Yamashita Turbine vane of steam turbine and steam turbine
US9488066B2 (en) * 2010-12-22 2016-11-08 Mitsubishi Hitachi Power Systems, Ltd. Turbine vane of steam turbine and steam turbine

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