US3834833A - Blade construction for axial-flow turbo-machines and method of protecting turbo-machine blades against stress corrosion cracking - Google Patents

Blade construction for axial-flow turbo-machines and method of protecting turbo-machine blades against stress corrosion cracking Download PDF

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Publication number
US3834833A
US3834833A US00333156A US33315673A US3834833A US 3834833 A US3834833 A US 3834833A US 00333156 A US00333156 A US 00333156A US 33315673 A US33315673 A US 33315673A US 3834833 A US3834833 A US 3834833A
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US
United States
Prior art keywords
blade
turbo
axial
stress corrosion
corrosion cracking
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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
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US00333156A
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English (en)
Inventor
G Faber
C Maggi
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.)
BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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BBC Brown Boveri France SA
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Publication date
Application filed by BBC Brown Boveri France SA filed Critical BBC Brown Boveri France SA
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Publication of US3834833A publication Critical patent/US3834833A/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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below

Definitions

  • the invention is directed to a procedure for protecting the hardened leading edge of blades or vanes (hereinafter blades) of axial-flow turbo-machines against stress corrosion cracking.
  • BACKGROUND INFORMATION It is general practice to harden the leading edges of blades of axial-flow turbo-machines for the purpose of minimizing erosion of the blades.
  • the desired hardness may be obtained by various heat treatments, for example by flame hardening or by means of induction heat by high frequency.
  • hardened steel is more susceptible to stress corrosion cracking sometimes referred to in the art as stress crack corrosion than is unhardened steel.
  • Stress corrosion is discussed in The Making, Shaping and Treating of Steel, United States Steel Corporation, 1964, page 933.
  • Hardened alloy steel for example stainless steel containing 12 percent of chromium, exhibits a particular great tendency towards stress corrosion cracking. This susceptibility is dependent on various factors, among others the composition and the heat treatment condition of the steel. Further, it is dependent on the contaminants, for example chlorides, which are present in the flowing working medium of the turbo-machine and also on the tensile stresses which act on the respectively endangered portion of the blade.
  • Another object of the invention is to achieve such protection by technological, as distinguished from constructive, measures.
  • the leading edge of such a blade is imparted with a permanent, compressive prestress in the direction of the longitudinal axis of the blade.
  • the blades may be imparted with the permanent compressive prestress in exceedingly simple manner.
  • hardening of steel is effected by heating to a temperature above 850C. and subsequent cooling or quenching. Due to the martensite formation in the steel, a volume increase takes place. If only a portion of a steel work piece is hardened in the indicated manner, as is the case in the hardening of the leading edge of a blade, then a compressive stress or prestress occurs in the hardened portion, provided the remainder of the work piece, which remains cold or unheated during'the hardening, has a sufficiently large'cross-sectional area in order to enable it to absorb the resulting tensile stresses without being plastically deformed, i.e. beyond the yield point.
  • the leading edge portion of the blade to be hardened is not permitted to have a cross-sectional area in excess of 20 percent of the total cross section of the blade and the thus remaining 80 percent are maintained in cold, unheated condition during the hardening, whereby the hardened portion is imparted with the desired permanent compressive prestress.
  • FIGURE of the drawing is a crosssectional view of a blade of an axial-flow turbomachine.
  • the cross-sectional area of the blade is formed by the portions 1 and 2, portion 1 being the cross-sectional area of the hardened zone, to wit, the area of the leading edge of the blade.
  • This hardened zone 1 extends not only adjacent the leading edge but also adjacent a portion of the suction side of the blade.
  • the area 2 occupies the remainder of the crosssectional area of the blade.
  • the crosssectional area 1 amounts to at the most, and preferably less than, 20 percent of the total cross-sectional area, to wit, the sum of the cross-sectional area 1 and 2.
  • the hardening of the area 1 may be: accomplished by any conventional tempering treatment as previously re ferred to.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Heat Treatment Of Articles (AREA)
US00333156A 1972-02-18 1973-02-16 Blade construction for axial-flow turbo-machines and method of protecting turbo-machine blades against stress corrosion cracking Expired - Lifetime US3834833A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH237372A CH564147A5 (zh) 1972-02-18 1972-02-18

Publications (1)

Publication Number Publication Date
US3834833A true US3834833A (en) 1974-09-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
US00333156A Expired - Lifetime US3834833A (en) 1972-02-18 1973-02-16 Blade construction for axial-flow turbo-machines and method of protecting turbo-machine blades against stress corrosion cracking

Country Status (11)

Country Link
US (1) US3834833A (zh)
AT (1) AT316963B (zh)
BE (1) BE795520A (zh)
CA (1) CA1009125A (zh)
CH (1) CH564147A5 (zh)
DE (1) DE2211830A1 (zh)
FR (1) FR2172727A5 (zh)
GB (1) GB1418136A (zh)
HU (1) HU165495B (zh)
NL (1) NL7302234A (zh)
SE (1) SE400579B (zh)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4385866A (en) * 1979-08-02 1983-05-31 Tokyo Shibaura Denki Kabushiki Kaisha Curved blade rotor for a turbo supercharger
US4778345A (en) * 1985-03-15 1988-10-18 Ngk Spark Plug Co., Ltd. Turbine rotor
US5120197A (en) * 1990-07-16 1992-06-09 General Electric Company Tip-shrouded blades and method of manufacture
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
US5620307A (en) * 1995-03-06 1997-04-15 General Electric Company Laser shock peened gas turbine engine blade tip
US5742028A (en) * 1996-07-24 1998-04-21 General Electric Company Preloaded laser shock peening
US6004102A (en) * 1995-12-09 1999-12-21 Abb Patent Gmbh Turbine blade for use in the wet steam region of penultimate and ultimate stages of turbines
US6155789A (en) * 1999-04-06 2000-12-05 General Electric Company Gas turbine engine airfoil damper and method for production
US6551064B1 (en) 1996-07-24 2003-04-22 General Electric Company Laser shock peened gas turbine engine intermetallic parts
US20070243071A1 (en) * 1995-03-06 2007-10-18 Mannava Seetha R Laser shock peened gas turbine engine compressor airfoil edges
US20130287580A1 (en) * 2012-04-27 2013-10-31 General Electric Company Stress corrosion cracking resistance in superalloys

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5591009A (en) * 1995-01-17 1997-01-07 General Electric Company Laser shock peened gas turbine engine fan blade edges
JPH11182204A (ja) * 1997-12-15 1999-07-06 Toshiba Corp タービン動翼

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB195050A (en) * 1922-03-18 1923-07-19 Bbc Brown Boveri & Cie Improvements in steam turbine blades, and in the method of manufacturing such blades
US2888244A (en) * 1956-05-24 1959-05-26 Thompson Ramo Wooldridge Inc Fluid directing member
US3148954A (en) * 1960-06-13 1964-09-15 Haas Irene Turbine blade construction
US3371908A (en) * 1965-11-02 1968-03-05 Tokyo Shibaura Electric Co Turbine blading components and process of producing the same
US3564689A (en) * 1967-05-26 1971-02-23 Boehler & Co Ag Geb Method of fabricating a turbine blade having a leading edge formed of weld metal
US3729345A (en) * 1967-06-11 1973-04-24 Mitsubishi Heavy Ind Ltd Method for making propellers of high-strength and high-toughness cast steel

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB195050A (en) * 1922-03-18 1923-07-19 Bbc Brown Boveri & Cie Improvements in steam turbine blades, and in the method of manufacturing such blades
US2888244A (en) * 1956-05-24 1959-05-26 Thompson Ramo Wooldridge Inc Fluid directing member
US3148954A (en) * 1960-06-13 1964-09-15 Haas Irene Turbine blade construction
US3371908A (en) * 1965-11-02 1968-03-05 Tokyo Shibaura Electric Co Turbine blading components and process of producing the same
US3564689A (en) * 1967-05-26 1971-02-23 Boehler & Co Ag Geb Method of fabricating a turbine blade having a leading edge formed of weld metal
US3729345A (en) * 1967-06-11 1973-04-24 Mitsubishi Heavy Ind Ltd Method for making propellers of high-strength and high-toughness cast steel

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4385866A (en) * 1979-08-02 1983-05-31 Tokyo Shibaura Denki Kabushiki Kaisha Curved blade rotor for a turbo supercharger
US4778345A (en) * 1985-03-15 1988-10-18 Ngk Spark Plug Co., Ltd. Turbine rotor
US5120197A (en) * 1990-07-16 1992-06-09 General Electric Company Tip-shrouded blades and method of manufacture
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
US5620307A (en) * 1995-03-06 1997-04-15 General Electric Company Laser shock peened gas turbine engine blade tip
US20070243071A1 (en) * 1995-03-06 2007-10-18 Mannava Seetha R Laser shock peened gas turbine engine compressor airfoil edges
US6004102A (en) * 1995-12-09 1999-12-21 Abb Patent Gmbh Turbine blade for use in the wet steam region of penultimate and ultimate stages of turbines
US5742028A (en) * 1996-07-24 1998-04-21 General Electric Company Preloaded laser shock peening
US6551064B1 (en) 1996-07-24 2003-04-22 General Electric Company Laser shock peened gas turbine engine intermetallic parts
US6155789A (en) * 1999-04-06 2000-12-05 General Electric Company Gas turbine engine airfoil damper and method for production
US20130287580A1 (en) * 2012-04-27 2013-10-31 General Electric Company Stress corrosion cracking resistance in superalloys

Also Published As

Publication number Publication date
DE2211830A1 (de) 1973-08-23
FR2172727A5 (zh) 1973-09-28
HU165495B (zh) 1974-09-28
NL7302234A (zh) 1973-08-21
SE400579B (sv) 1978-04-03
AU5228873A (en) 1974-08-22
GB1418136A (en) 1975-12-17
CH564147A5 (zh) 1975-07-15
CA1009125A (en) 1977-04-26
AT316963B (de) 1974-08-12
BE795520A (fr) 1973-06-18

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