US2256479A - Blade for rotary machines operated by high temperature media - Google Patents

Blade for rotary machines operated by high temperature media Download PDF

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Publication number
US2256479A
US2256479A US262454A US26245439A US2256479A US 2256479 A US2256479 A US 2256479A US 262454 A US262454 A US 262454A US 26245439 A US26245439 A US 26245439A US 2256479 A US2256479 A US 2256479A
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US
United States
Prior art keywords
blade
core
shell
temperature
cooling
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
US262454A
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English (en)
Inventor
Holzwarth 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.)
HOLZWARTH GAS TURBINE CO
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HOLZWARTH GAS TURBINE CO
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.)
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Application filed by HOLZWARTH GAS TURBINE CO filed Critical HOLZWARTH GAS TURBINE CO
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Publication of US2256479A publication Critical patent/US2256479A/en
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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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the present invention relates to the blading V More specifically, it is an object oi the invention to provide a blade having such a high heat conductivity from the free, outer tip to the base or. foot of the blade that adequate cooling of the blade may be accomplished by conducting a cooling agent in contact with substantially only the foot portion of the blade, and even when the cooling is of the hot type, that is, employs a. cooling agent at a .temperature considerably above room temperature, such as water at a temperature near its boiling point at superatmospheric pressure.
  • the volume of the shell material is made approximately equal to or less than the above mentioned critical value.
  • This critical ratio of shell volume to core volume is generally approximately equal to 4. This value is valid for all practical combinations of a highly heat-resistant shell material, that is, a material having a high strength at high temperatures, the shell acting as carrier for the core, and a highly heat-conducting core material, that is, a material having a heat conductivity -of the order of that of copper.
  • My invention thus makes it possible to build a stator or rotor blade with a. larger proportion of the cheaper, though mechanically weaker, core material such as copper, because the lower shell temperature signifies a stronger shell, the blade being thus able to withstand the stresses imposed thereon in operation in spite of the reduced mass of the shell material.
  • Fig. 1 shows the temperature curve at the blade tip in dependence upon the relationship of the space or volume occupied by the building material of higher heat resistance (shell material) to that occupied by the core wa Rx both with reference to the free blade length exposed to the working medium, while Fig. 2 represents in similar fashion the corresponding blade foot temperatures.
  • Fig. 3 illustrates a horizontal section through a guide or reversing blade constructed in accordance with the invention and taken along the lines III-III of Fig. 4.
  • Fig. 4 represents a vertical longitudinal section through the blade along the line IV-IV of Fig. 3.
  • Fig. 5 shows a section running vertically to the turbine wheel axis through a series of juxtaposed reversing blades of a conbustion gas turbine along the lines VV of Figs. 3 and 4.
  • Fig. 6 illustrates a modified form of mounting of the stator or reversing blade :1 while Fig. 7 shows a general schematic view, partly in section, of an explosion turbine plant having my improved blade construction embodied therein :[n the graph shown in Fig. 1, the proportion RWB x represents the abscissa, RwB corresponding to the space occupied by the working material of higher heat resistance, that is the outer shell, and RK the space occupied by the building material of higher heat conductivity or core.
  • the ordinates drawn through the zero point of the co-ordinate system thus represent the temperature conditions in a blade which consists only of a good heat conductor, thus for example, only of copper; while the ordinate belonging to the abscissa point 00 represents the temperature course of a coreless blade, that is, of a blade which consists only of the building material of high heat resistance.
  • Figs. 3 to 5 illustrate such a blade constructed in accordance with the invention. It will be seen that the core I of copper or other equally highly heat-conducting material, in order to possess the necessary increased space relationship to the building material of higher heat resistance 2, no longer has a circular cross-section but rather one more nearly fitted to the blade cross-section perpendicular to the longitudinal blade axis.
  • the copper core I may be extended into the cooling space 3 which conducts the cooling agent destined for the blade cooling.
  • the core extension 4 may be considerably widened with respect to the core I so that, particularly by the arrangement of grooves 5, cooling surfaces t of large surface area are created to an extent which affords unhindered heat conduction from the blade foot.
  • the blade is welded to the adjoining walls I of the cooling chamber 3, the welding joints being shown at 8 as reinforcing anchors for the blades.
  • Water under particularly high pressure is suitable as cooling agent, the same being evaporated by the absorption of heat and yielding steam for the production of work. As explained below, the water may be heated to nearly the boiling point at high pressure in the cooling chambers and then caused to form steam upon reduction of the pressure.
  • the base 'of the blade is provided with slots at the sides thereof which are adapted to receive flanges or extensions la of the wall I constituting the support or part of the support of the blades.
  • the flanges la act as anchoring members.
  • the blades are inserted in a suitable break in the flanges and are slid therealong to their flnal position. In such position they may be welded to the flanges, and in order to fix the blades more firmly and at the same time provide additional conducting connections with the support, rings lb may be wedged or welded (in two or more sections) into the spaces between the blade and wall i above the flanges la, 1. e. inwardly radially in the case of stator blades.
  • blade constructions of the type illustrated not only is the foot of the blade adequately cooled, but the exposed tip of the blade is maintained at a sufliciently low temperature to prevent injury thereto by the hot gases.
  • This blade tip temperature is kept within safe limits, even in the case of long blades, by making the volume of the shell of the exposed portion of the blade no greater than about 4 times the volume of the core; thus the average cross-section of the shell in a plane perpendicular to the longitudinal axis of the blade may be made equal to about 4 times or less than 4 times the cross-section of the core.
  • the core may be made of copper or other superior heat-conducting metal, copper being highly satisfactory as it conducts heat '7 times better than iron and about 11 times better than heat-resisting alloys; while the shell may be made of tungsten or tungsten-containing alloys or of other heat-resisting metals or alloys.
  • FIG. 7 One of a plurality of explosion chambers 9, working out of phase, is illustrated in Fig. '7, the chamber being provided with a scavenging air inlet valve ID, a fuel inlet member Ii and an additional valve I2 for air of higher pressure for eifecting atomization of a liquid fuel.
  • the outlet valve l3 efiects discharge of the high temperature, high pressure gases generated by the explosion, brought about by the spark plugs ll, of an ignitable mixture of air and fuel in the chamber 9, the gases being directed by suitable nozzles to the first or impulse wheel. l5. From the latter they flow. preferably after intermediate equalization of their pressure,
  • the guide or stator blades 2 are in heat-conducting connection with the wall I forming part of a cooling jacket III which is connected by pipe it with an evaporator or steam separator 20.
  • the separate steam of high pressure is withdrawn by the conduit 2
  • the water supply is replenished by a feed water pump 25 which is connected with the interior of the evaporator 20 by the pipe 26.
  • the invention is of particular value for stator or reversing blades of combustion turbines, as such blades are continuously subjected to the action of the hot gases, whereas the rotor blades, in so far as the rotor is not a full admission rotor (i. e. impinged over 360) have an opportunity to cool outside the nozzle arc, such cooling being increased by ventilation.
  • the advantages of my invention are of particular significance in the case of hot" cooling. This hot cooling has the advantage that the average temperature of the cooling agent is increased.
  • the average cooling agent temperature As the upper permissible cooling temperature is limited in view of the danger of steam formation, the average cooling agent temperature, on the other hand, being lower than the maximum temperature by half the difference between the inlet and outlet temperatures, the average cooling agent temperature is higher the lower this difference is. Maintaining the average cooling agent temperature high is important for the reason that the heat transfer to the wheel and to the blades falls considerably with increasing avarage cooling agent temperature. The heat losses to the wheel thus become smaller and the efliciency of the gas turbine becomes better the higher the average cooling agent temperature can be maintained, it being of advantage to employ the hot cooling and take into account the increased temperature stresses resulting therefrom.
  • the increase in the size of the core should not, of course, be carried to the point at which the strength of the blade and particularly of the shell is impaired.
  • the shell will in all cases remain as the strength-providing element of the blade.
  • shell as used herein is not to be understood as being limited to a member which completely encases the core. In certain blade constructions the "shell may be created only along the faces of the blade swept by the gases: thus at the farther side of the blades considered from the nozzles, the core may reach to the outer surface provided that it is sufliciently heatresisting.
  • a blade according to claim 1 wherein the cross-section of the carrying outer body referred to the free blade length exposed to the working medium and in a plane perpendicular to the longitudinal axis of the blade, is approximately equal to, or smaller than, four times the crosssection occupied by the material of higher heat conductivity.
  • a rotary machine having a blade as defined in claim 1 and including, in combination, means providing a cooling chamber at the foot of the blade, and conduits for supplying a cooling agent to and withdrawing the same from said chamber, the heat conducting core being lengthened to extend into the cooling space and into contact with the cooling agent.
  • a rotary machine having a blade as defined in claim 1 and including, in combination, means providing a cooling chamber at the foot of the blade, and conduits for supplying a cooling agent to and withdrawing the same from said chamber.
  • the heat conducting core being lengthened to extend into the cooling space and into contact with the cooling agent, the cross-section of the core extension lying in the path of the cooling agent being greater than that of the core within the exposed portion of the blade.
  • a series of blades and a support for such blades, at least certain of said blades being composed of an outer shell made of a material having a high strength at high temperatures but of relatively lower heat conductivity, and a core of relatively higher heat conductivity of the order of that of copper, the volume occupied by the shell being no greater than about four times the volume occupied by the core in the exposed portion of the blade, said shell being made of such material and being so shaped that it is capable of transmitting to the support the forces imposed thereon during the operation of the machine.
  • a heat resisting blade for use in machines operating with a high temperature medium comprising an outer shell made of a metallic material having a high strength at high temperatures, and a core made of a metal of greater heat conductivity than the material of the outer shell and of the order of that of copper, the volume of the material composing the shell being approximately equal to or less than four times the volume occupied by the core in the portion of the blade exposed to the hot medium.
  • a series of blades and a support for such blades, at least certain of said blades being composed of an outer shell made of a material having a high strength at high temperatures but of relatively lower heat conductivity, and a core of relatively higher heat conductivity by the order of that of copper, the volume occupied by the shell being no greater than about four times the volume occupied by the core, said shell being capable of transmitting to the support the forces imposed thereon during the operation of the machine, said support being provided with a cooling space at the base of the blade, and means for introducing a cooling agent into said space to eflect cooling of the blade by way of the foot thereof.
  • cooling agent is water
  • the cooling agent is water
  • the cooling agent including an evaporator, a conduit connecting the cooling space with the evaporator, a conduit for returning unevaporated water from the evaporator to the cooling space and means for withdrawing the separated steam from the evaporator.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US262454A 1938-03-21 1939-03-17 Blade for rotary machines operated by high temperature media Expired - Lifetime US2256479A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE526590X 1938-03-21

Publications (1)

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US2256479A true US2256479A (en) 1941-09-23

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Country Status (4)

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US (1) US2256479A (enrdf_load_stackoverflow)
FR (1) FR851823A (enrdf_load_stackoverflow)
GB (1) GB526590A (enrdf_load_stackoverflow)
NL (1) NL49923C (enrdf_load_stackoverflow)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2501038A (en) * 1947-03-29 1950-03-21 United Aircraft Corp Mounting for hollow turbine blades
US2510735A (en) * 1946-04-10 1950-06-06 United Aircraft Corp Turbine element
US2589239A (en) * 1945-05-16 1952-03-18 Malcolm Mitchell Turbine-compressor unit
US2699917A (en) * 1946-08-24 1955-01-18 Thompson Prod Inc Turbine wheel and blade construction
US2783966A (en) * 1948-10-22 1957-03-05 Maschf Augsburg Nuernberg Ag Parts for machinery
US2873087A (en) * 1952-05-20 1959-02-10 Parsons & Marine Eng Turbine Means for cooling gas turbines
US3166295A (en) * 1959-08-24 1965-01-19 Zakl Mech Im Gen K S Guide wheel for condensing turbines of great and greatest power
US3500935A (en) * 1967-08-31 1970-03-17 Nat Foam System Inc Turbine-powered high-expansion foam generator
US5191711A (en) * 1991-12-23 1993-03-09 Allied-Signal Inc. Compressor or turbine blade manufacture
EP1647671A1 (de) * 2004-10-13 2006-04-19 Siemens Aktiengesellschaft Thermisch beanspruchtes Bauteil einer Strömungsmaschine
EP2908010A3 (de) * 2014-01-28 2015-10-21 NEUMAN & ESSER GmbH & Co. KG Kolbenstange für Kolbenkompressoren und Kolbenkompressor
FR3074519A1 (fr) * 2017-12-04 2019-06-07 Safran Aircraft Engines Piece tournante pour turbomachine

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2589239A (en) * 1945-05-16 1952-03-18 Malcolm Mitchell Turbine-compressor unit
US2510735A (en) * 1946-04-10 1950-06-06 United Aircraft Corp Turbine element
US2699917A (en) * 1946-08-24 1955-01-18 Thompson Prod Inc Turbine wheel and blade construction
US2501038A (en) * 1947-03-29 1950-03-21 United Aircraft Corp Mounting for hollow turbine blades
US2783966A (en) * 1948-10-22 1957-03-05 Maschf Augsburg Nuernberg Ag Parts for machinery
US2873087A (en) * 1952-05-20 1959-02-10 Parsons & Marine Eng Turbine Means for cooling gas turbines
US3166295A (en) * 1959-08-24 1965-01-19 Zakl Mech Im Gen K S Guide wheel for condensing turbines of great and greatest power
US3500935A (en) * 1967-08-31 1970-03-17 Nat Foam System Inc Turbine-powered high-expansion foam generator
US5191711A (en) * 1991-12-23 1993-03-09 Allied-Signal Inc. Compressor or turbine blade manufacture
EP1647671A1 (de) * 2004-10-13 2006-04-19 Siemens Aktiengesellschaft Thermisch beanspruchtes Bauteil einer Strömungsmaschine
EP2908010A3 (de) * 2014-01-28 2015-10-21 NEUMAN & ESSER GmbH & Co. KG Kolbenstange für Kolbenkompressoren und Kolbenkompressor
US9869312B2 (en) 2014-01-28 2018-01-16 Neuman & Esser Gmbh & Co. Kg Piston rod for a piston compressor, and the piston compressor
FR3074519A1 (fr) * 2017-12-04 2019-06-07 Safran Aircraft Engines Piece tournante pour turbomachine

Also Published As

Publication number Publication date
GB526590A (en) 1940-09-20
NL49923C (enrdf_load_stackoverflow) 1941-02-15
FR851823A (fr) 1940-01-16

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