US2977089A - Heat responsive means for blade cooling - Google Patents

Heat responsive means for blade cooling Download PDF

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US2977089A
US2977089A US841425A US84142559A US2977089A US 2977089 A US2977089 A US 2977089A US 841425 A US841425 A US 841425A US 84142559 A US84142559 A US 84142559A US 2977089 A US2977089 A US 2977089A
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blade
compartments
turbine
valve
fluid
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US841425A
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Daniel J Mccarty
Edward H Lutz
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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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Definitions

  • This invention relates to means of controlling the local temperatures in turbines.
  • An object of this invention is a cooling system for turbines wherein the danger of hot-spots is eliminated.
  • a further object of this invention is a system wherein a turbine runs at maximum efliciency by operating at a constant temperature under varying conditions.
  • a still further object of this invention is a cooling system which automatically controls the amount of cooling fluid passing through the hot turbine.
  • Figure l is a cross-sectional view of a turbine showing the details of the cooling systems
  • Figure 1A is a cross-sectional view of a fragment of a turbine complementary to that of Figure 1 showing a modification of the invention
  • Figure 2 is a modification of the location of the cooling system control unit
  • FIG. 3 is a modification of the cooling system control unit and valve
  • Figure 4 is a cross-sectional view along section lines 4-4 of Figure 1, and
  • FIG. 5 is a further modification of the cooling system control unit.
  • a turbine 1 comprises a solid rotor, 2, having on its periphery a plurality of blades 4. Encompassing the turbine is a casing 3 providing a housing for the turbine rotor and means for suspending the stator blades.
  • Forward and rear rotor blades 4 are hollow, which construction is well known. Forward blades 4 are divided by a transverse wall 5 commencing from the root of the blade and terminating just short of the tip 44 thereby 2. dividing the blade into two compartments 46 and 47, with an open passage 48 at the tip joining the compartments. Within each blade a build up portion 6, extending from 'the root, has a plurality of ports 6 therein; one port for each compartment.
  • a bimetallic leaf 8 is secured at its mid-point to the wall 40 and extends over both ports 6.
  • a coolant feed line 41 leads into one of the compartments via passage 14 and return line'42 is connected to the other of the compartments via passage 13. i
  • the blades are secured to shroud ring 27 and to the inner ring 43.
  • the blade is divided into two compartments by a transverse partition 22 in which is provided a passage 23.
  • the port is covered by a bimetallic strip 24 fastened at one end by a rivet 60 to the partition wall.
  • a conduit 15 feeds cooling fluid into one of the compartments while conduit 16 returns the fluid back to the source.
  • FIG. 1A A further modification of the valve means is shown in Figure 1A.
  • a partition wall 12 divides the blade into two compartments 49 and 51 with a passageway 52 at the tip 44 of the blade connecting the compartments, while in the stator stage, blade 21 has a partition Wall 25 dividing theblade into two similar compartments.
  • Conduits 17 and 18 lead intothe compartments at the root of the stator bladefconduits 9 and 10 lead into the compartments at the root of the rotor blade.
  • Both compartment entry ports are covered by a bimetallic element, element 11 in the rotor blade and element 26 in the stator blade. Each element is connected at its mid-point to its respective partition wall and its respective blade root 56 and 59.
  • FIG. 2 illustrates a further modification of the valve means.
  • Conduit 19 feeds in'and conduit 20, discharges from the compartments 54 and 55, respectively; recessed adjacent an opening of one of the compartments is a bimetallic element 28; the other opening is not serviced with a bimetallic element and fluid passes freely through the port.
  • FIG. 3 a further modification of the valve means is shown.
  • the blade root or shroud ring has attached thereto the bimetal element 29 via a rivet 33.
  • Feed line 32 terminates in a countersunk section 31 and a matching truncated nipple or valve element 30 is fastened to the When the opening is closed, recess 31 accommodates valve element 30 preventing a passage of fluid; when the valve is open, element 30 is clear of the recess 31 providing an opening for the passage of fluid.
  • FIG. 5 shows still a further modification.
  • conduits 36 and 37 are connected to the two compartments 57 and 58.
  • Valve 50 is maintained in its recess by the action magnet 34 which functions as a valve seat and has an aperture 64 through which cooling fluid from conduit 36 enters compartment 57.
  • the spring 35 is secured by means of rivets 68 and 70 to the valve 50 and partition wall 66, respectively.
  • a passage 66 in wall 70 is provided to interconnect compartments 57 and 58.
  • the cooling fluid may be connected to any type of cooler 38 well known in the art or it may be directed externally of the turbine to atmosphere if the fluid is air.
  • the bimetallic valve When the temperature of the cooling fluid starts to increase above a predetermined range of temperatures, the bimetallic valve slowly starts to turn thus slowly uncovering the associated passage. A similar action occurs if a hot spot begins to develop in one, of the blades. The bimetallic element/ s of that blade further open the valve allowing additional cooling fluid to circulate through the blade, thus cooling it more than the adjacent blades.
  • valves In a steady state condition, the valves are partially open allowing a percentage of maximum fiow to go through. If the valves begin to heat up, the bimetallic valves open further allowing additional fluid to pass through; if the valves tend to cool somewhat, the bimetallic valves tend to close thereby restricting the flow of fluid and the blades have a tendency to return to the temperature of the steady state condition.
  • the magnet 34 functions in a manner similar to the bimetallic valve.
  • the magnetic action fluctuates under the action of the heated fluid thereby allowing the bias action of the spring to come into play.
  • valve means may be used for both the stator and rotor blades or the blades of the rotor may have one type of bimetal and valve and the blades of the stator have another modification of the bimetal and valve.
  • a partition wall in said hollow blade extending substantially longitudinally thereof from said root portion and thereby forming a pair of compartments within said hollow blade, said partition wall terminating in advance of said tip portion of said hollow blade to thereby provide a passageway between said pair of compartments, said hollow blade having a fiuid inlet in said root portion to accommodate the entry of cooling fluid into one of said compartments and having a fluid outlet in said root portion to accommodate the discharge of cooling fluid from the other of said compartments, a magnetic valve seat carried within said one compartment, and a spring biased valve member carried with said one compartment and being movable between open and closed positions relative to said magnetic valve seat in response to changes in the temperature of thecooling fluid flowing through said hollow blade to thereby maintain said blade at a substantially constant predetermined temperature.
  • valve member is carried by a spring one end of which is rigidly connected to said partition wall and the opposite end of which is rigidly connected to said valve member, said spring being operable to constantly urge said valve member toward said open position.

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

Description

March 28, 1961 D. J. M CARTY ETAL 2,977,089
HEAT RESPONSIVE MEANS FOR BLADE COOLIVNG Original Filed June 12, 1956 1..7'... VIII...
Q N Q INVENTOR.
52/4/70 6 A07: @A lel. J/k (/JFI'Y BY United States Patent HEAT RESPQNSIVE MEANS or; BLADE COOLING Daniel J. McCarty, Drexel Hill, and Edward H. Lutz, Nor'wood, PaQ, assignors, by theme assignments, to the United States of America as represented by the Secretary of the Navy Original application June 12, 1956, Ser. No. 591,002, now Patent No. 2,906,494, dated Sept. 29, 1959. Di-v vided and this application July 31, 1959, Ser. No. 841,425
3 Claims. (Cl. 253--39.15)
This application is a division of co-pending application Serial No. 591,002, filed June 12 1956, now Patent No. 2,906,494, granted Sept. 29, 1959'.
This invention relates to means of controlling the local temperatures in turbines.
In order to insure the maximum efficiency of any turbine, gas or steam, it is necessary that the turbine operate at a constant uniform temperature. Solid type blading is often used in a turbine where the maximum temperature of the passing gas or steam is not too high. However, in modern day turbines, the temperatures of the fluids passing through the turbine are very high and cooling means for the various parts of the turbine must be provided to reduce the temperature thereof. Even with such cooling means, hot spots develop, due to the very high temperatures of the passingfluids, in isolated sections of the turbine that are diflicult to cool.
A further disadvantage occurs with the cooling systems presently in use in that the amount of cooling is kept constant and no automatic compensation is made. for differences in temperature between the blading and the passing fluids. As a result of this, at times the turbine runs at something less than maximum efliciency.
An object of this invention, therefore, is a cooling system for turbines wherein the danger of hot-spots is eliminated.
A further object of this invention is a system wherein a turbine runs at maximum efliciency by operating at a constant temperature under varying conditions.
A still further object of this invention is a cooling system which automatically controls the amount of cooling fluid passing through the hot turbine.
These and additional objects will be readily apparent to those skilled in the art from a perusal of the following disclosure and an examination of the enclosed drawings wherein:
Figure l is a cross-sectional view of a turbine showing the details of the cooling systems,
Figure 1A is a cross-sectional view of a fragment of a turbine complementary to that of Figure 1 showing a modification of the invention,
Figure 2 is a modification of the location of the cooling system control unit,
Figure 3 is a modification of the cooling system control unit and valve,
Figure 4 is a cross-sectional view along section lines 4-4 of Figure 1, and
Figure 5 is a further modification of the cooling system control unit.
In Figure 1, a turbine 1 comprises a solid rotor, 2, having on its periphery a plurality of blades 4. Encompassing the turbine is a casing 3 providing a housing for the turbine rotor and means for suspending the stator blades.
Forward and rear rotor blades 4 are hollow, which construction is well known. Forward blades 4 are divided by a transverse wall 5 commencing from the root of the blade and terminating just short of the tip 44 thereby 2. dividing the blade into two compartments 46 and 47, with an open passage 48 at the tip joining the compartments. Within each blade a build up portion 6, extending from 'the root, has a plurality of ports 6 therein; one port for each compartment.
A bimetallic leaf 8 is secured at its mid-point to the wall 40 and extends over both ports 6. A coolant feed line 41 leads into one of the compartments via passage 14 and return line'42 is connected to the other of the compartments via passage 13. i
In the stator blade 21, Figures 1 and 4, preceding the above turbine rotor stage, the blades are secured to shroud ring 27 and to the inner ring 43. The blade is divided into two compartments by a transverse partition 22 in which is provided a passage 23. The port is covered by a bimetallic strip 24 fastened at one end by a rivet 60 to the partition wall. A conduit 15 feeds cooling fluid into one of the compartments while conduit 16 returns the fluid back to the source.
A further modification of the valve means is shown in Figure 1A. In the rotor blade 4 a partition wall 12 divides the blade into two compartments 49 and 51 with a passageway 52 at the tip 44 of the blade connecting the compartments, while in the stator stage, blade 21 has a partition Wall 25 dividing theblade into two similar compartments. Conduits 17 and 18 lead intothe compartments at the root of the stator bladefconduits 9 and 10 lead into the compartments at the root of the rotor blade. Both compartment entry ports are covered by a bimetallic element, element 11 in the rotor blade and element 26 in the stator blade. Each element is connected at its mid-point to its respective partition wall and its respective blade root 56 and 59. A
Figure 2 illustrates a further modification of the valve means. Conduit 19 feeds in'and conduit 20, discharges from the compartments 54 and 55, respectively; recessed adjacent an opening of one of the compartments is a bimetallic element 28; the other opening is not serviced with a bimetallic element and fluid passes freely through the port.
In Figure 3 a further modification of the valve means is shown. The blade root or shroud ring has attached thereto the bimetal element 29 via a rivet 33. Feed line 32 terminates in a countersunk section 31 and a matching truncated nipple or valve element 30 is fastened to the When the opening is closed, recess 31 accommodates valve element 30 preventing a passage of fluid; when the valve is open, element 30 is clear of the recess 31 providing an opening for the passage of fluid.
Figure 5 shows still a further modification. In this figure, conduits 36 and 37 are connected to the two compartments 57 and 58. Valve 50 is maintained in its recess by the action magnet 34 which functions as a valve seat and has an aperture 64 through which cooling fluid from conduit 36 enters compartment 57. When the temperature of the fluid increases, the magnet loses some of its retaining properties and the spring 35 forces the valve 50 to its open position. The spring 35 is secured by means of rivets 68 and 70 to the valve 50 and partition wall 66, respectively. A passage 66 in wall 70 is provided to interconnect compartments 57 and 58.
The cooling fluid may be connected to any type of cooler 38 well known in the art or it may be directed externally of the turbine to atmosphere if the fluid is air.
Operation All of the modifications illustrated, except that of Figure 5, operate basically in the same manner. If the temperature of the cooling fluid is low, the bimetallic element in each of the modifications covers the fluid inlet port or the element covers both the inlet and outlet ports,
When the temperature of the cooling fluid starts to increase above a predetermined range of temperatures, the bimetallic valve slowly starts to turn thus slowly uncovering the associated passage. A similar action occurs if a hot spot begins to develop in one, of the blades. The bimetallic element/ s of that blade further open the valve allowing additional cooling fluid to circulate through the blade, thus cooling it more than the adjacent blades.
In a steady state condition, the valves are partially open allowing a percentage of maximum fiow to go through. If the valves begin to heat up, the bimetallic valves open further allowing additional fluid to pass through; if the valves tend to cool somewhat, the bimetallic valves tend to close thereby restricting the flow of fluid and the blades have a tendency to return to the temperature of the steady state condition.
In the modification of Figure 5, the magnet 34 functions in a manner similar to the bimetallic valve. The magnetic action fluctuates under the action of the heated fluid thereby allowing the bias action of the spring to come into play. f
While several modifications of the basic temperature control system are shown in Figure 1, it is of course understood that one type of valve means may be used for both the stator and rotor blades or the blades of the rotor may have one type of bimetal and valve and the blades of the stator have another modification of the bimetal and valve.
Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.
What is claimed is:
1. In a turbine having a hollow, fluid-cooled blade with said blade having a tip portion and a root portion, a partition wall in said hollow blade extending substantially longitudinally thereof from said root portion and thereby forming a pair of compartments within said hollow blade, said partition wall terminating in advance of said tip portion of said hollow blade to thereby provide a passageway between said pair of compartments, said hollow blade having a fiuid inlet in said root portion to accommodate the entry of cooling fluid into one of said compartments and having a fluid outlet in said root portion to accommodate the discharge of cooling fluid from the other of said compartments, a magnetic valve seat carried within said one compartment, and a spring biased valve member carried with said one compartment and being movable between open and closed positions relative to said magnetic valve seat in response to changes in the temperature of thecooling fluid flowing through said hollow blade to thereby maintain said blade at a substantially constant predetermined temperature.
2. In a turbine as claimed in claim 1 wherein said magnetic valve seat is carried within said orie compart ment at the rootportion of said blade.
3. In a turbine as claimed in claim 1 wherein said valve member is carried by a spring one end of which is rigidly connected to said partition wall and the opposite end of which is rigidly connected to said valve member, said spring being operable to constantly urge said valve member toward said open position.
References Cited in the file of this patent UNITED .STATES PATENTS 1,887,717 Koch Nov. 15, 1932 2,339,087 Mantz Jan. -11, 1944 2,601,579 Wittmann June 24, 1952 2,618,120 Papini Nov, 18, 1952 2,778,601 Eckert Jan. 22, 1957 2,787,440 Thompson Apr. 2, 1957 FOREIGN PATENTS 369,996 Germany Feb. 23, 1923 mam
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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5022817A (en) * 1989-09-12 1991-06-11 Allied-Signal Inc. Thermostatic control of turbine cooling air
FR2672338A1 (en) * 1991-02-06 1992-08-07 Snecma Turbine vane equipped with a cooling system
US5249618A (en) * 1991-01-30 1993-10-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Method of making a complex ceramic core for use in metal casting process
US6485255B1 (en) * 1999-09-18 2002-11-26 Rolls-Royce Plc Cooling air flow control device for a gas turbine engine
US6491495B1 (en) * 2000-03-02 2002-12-10 Hitachi Ltd. Closed circuit blade-cooled turbine
US7547190B1 (en) 2006-07-14 2009-06-16 Florida Turbine Technologies, Inc. Turbine airfoil serpentine flow circuit with a built-in pressure regulator
FR2968718A1 (en) * 2010-12-10 2012-06-15 Snecma TURBOREACTOR COMPRISING A COOLING AIR COLLECTION SYSTEM WITH AUTOMATIC FLOW VARIATION VARIATION
WO2013176863A1 (en) 2012-05-22 2013-11-28 United Technologies Corporation Passive thermostatic valve
US8926289B2 (en) 2012-03-08 2015-01-06 Hamilton Sundstrand Corporation Blade pocket design
WO2018164598A1 (en) * 2017-03-09 2018-09-13 Siemens Aktiengesellschaft Supply system of gas turbine component cooling
US10724376B2 (en) * 2018-02-08 2020-07-28 General Electric Company Airfoil having integral fins

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE369996C (en) * 1919-12-27 1923-02-26 Alexander Loczy Dipl Ing Device for blade cooling for gas turbines
US1887717A (en) * 1923-09-01 1932-11-15 Charles N Koch Combustion turbine
US2339087A (en) * 1939-06-30 1944-01-11 Milwaukee Gas Specialty Co Thermostatic control device
US2601579A (en) * 1948-05-22 1952-06-24 Robert A Wittmann Curie point valve
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
US2778601A (en) * 1951-05-28 1957-01-22 Ernst R G Eckert Fluid cooled turbine blade construction
US2787440A (en) * 1953-05-21 1957-04-02 Westinghouse Electric Corp Turbine apparatus

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE369996C (en) * 1919-12-27 1923-02-26 Alexander Loczy Dipl Ing Device for blade cooling for gas turbines
US1887717A (en) * 1923-09-01 1932-11-15 Charles N Koch Combustion turbine
US2339087A (en) * 1939-06-30 1944-01-11 Milwaukee Gas Specialty Co Thermostatic control device
US2618120A (en) * 1946-06-07 1952-11-18 Papini Anthony Coaxial combustion products generator and turbine with cooling means
US2601579A (en) * 1948-05-22 1952-06-24 Robert A Wittmann Curie point valve
US2778601A (en) * 1951-05-28 1957-01-22 Ernst R G Eckert Fluid cooled turbine blade construction
US2787440A (en) * 1953-05-21 1957-04-02 Westinghouse Electric Corp Turbine apparatus

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5022817A (en) * 1989-09-12 1991-06-11 Allied-Signal Inc. Thermostatic control of turbine cooling air
US5249618A (en) * 1991-01-30 1993-10-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Method of making a complex ceramic core for use in metal casting process
FR2672338A1 (en) * 1991-02-06 1992-08-07 Snecma Turbine vane equipped with a cooling system
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
US6485255B1 (en) * 1999-09-18 2002-11-26 Rolls-Royce Plc Cooling air flow control device for a gas turbine engine
US7029236B2 (en) 2000-03-02 2006-04-18 Hitachi, Ltd. Closed circuit blade-cooled turbine
US6746208B2 (en) 2000-03-02 2004-06-08 Hitachi, Ltd. Closed circuit blade-cooled turbine
US20040170494A1 (en) * 2000-03-02 2004-09-02 Hitachi, Ltd. Closed circuit blade-cooled turbine
US6491495B1 (en) * 2000-03-02 2002-12-10 Hitachi Ltd. Closed circuit blade-cooled turbine
US7547190B1 (en) 2006-07-14 2009-06-16 Florida Turbine Technologies, Inc. Turbine airfoil serpentine flow circuit with a built-in pressure regulator
FR2968718A1 (en) * 2010-12-10 2012-06-15 Snecma TURBOREACTOR COMPRISING A COOLING AIR COLLECTION SYSTEM WITH AUTOMATIC FLOW VARIATION VARIATION
US9062605B2 (en) 2010-12-10 2015-06-23 Snecma Turbojet including an automatically variable flow rate bleed circuit for cooling air
US8926289B2 (en) 2012-03-08 2015-01-06 Hamilton Sundstrand Corporation Blade pocket design
WO2013176863A1 (en) 2012-05-22 2013-11-28 United Technologies Corporation Passive thermostatic valve
EP2852734A4 (en) * 2012-05-22 2016-04-27 United Technologies Corp Passive thermostatic valve
WO2018164598A1 (en) * 2017-03-09 2018-09-13 Siemens Aktiengesellschaft Supply system of gas turbine component cooling
US10724376B2 (en) * 2018-02-08 2020-07-28 General Electric Company Airfoil having integral fins

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