US2782000A - Gas-turbine - Google Patents
Gas-turbine Download PDFInfo
- Publication number
- US2782000A US2782000A US264120A US26412051A US2782000A US 2782000 A US2782000 A US 2782000A US 264120 A US264120 A US 264120A US 26412051 A US26412051 A US 26412051A US 2782000 A US2782000 A US 2782000A
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- United States
- Prior art keywords
- rotor
- rotor blades
- axial direction
- row
- unit
- Prior art date
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- Expired - Lifetime
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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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
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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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
- F01D5/088—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in a closed cavity
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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
- F01D5/185—Liquid cooling
Definitions
- the invention relates to a device for cooling the blades in gas turbines.
- the cooling is intended primarily for blades subjected to high temperature stressing beyond 700 C. and is effected in a manner known per se by an evaporating liquid, which is caused to circulate by the action of centrifugal force by means of longitudinal bores in the blade.
- each axial row of blades has associated therewith a heat exchanger, which i independent of the heat exchangers of the other rows of blades- Consequently axial rows of blades can be removed easily together with the heat exchanger.
- the association of a heat exchanger with an axial row of blades enables also a special construction, which in accordance with the invention consists in that the heat exchanger associated with each row of blades are axially spaced from the blade rings. Therefore it is no longer necessary to conduct the secondary cooling medium axially through the rotor; on the contrary, that medium may be reversed within or behind the sets of coolers so as to emerge at the same end olthe rotor body where his admitted.
- Fig. 1 shows by way of example an embodiment of the invention in an axial section taken through the upper'half thereof, in the case of air being used as a secondary cooling medium
- FIG. 2 is a fragmentary transverse sectional view illustrating a system of detachable units according to the present invention on an enlargedscale
- Fig. 3 shows the arrangement in the case of a liquid secondary cooling medium, particularly water, being used.
- Fig. 1 is the casing of the turbine with the guide blades 5
- 2 is the rotor with the rotor blades 11.
- the hot gases enter at 3 the blade ring formed by the guide and rotor blades, and pass off at 4.
- each rotor blade has passage means including central bores 13-and a larger number of peripheral bores 12, which communicate witheacb other at the blade top.
- the cooler cooling medium of higher specific gravity, flows outwardly under centrifugal force, i heated or evaporated, and when its specific gravity has thus been reduced the medium is forced inwardly.
- Each conduit means it communicates with the passages 12, 13 in the rotor blades of the respective row, and with the passage of a heat exchanger 10 which is secured to the tubes having cooling fins and being inserted with the undercut roots 23 thereof into corresponding axially extending grooves 29 which are formed in the cavity 14 of the rotor body.
- the cavity 14 shown in Fig. l is closed by a means 27 provided with an inlet 31 and an outlet 32, respec tively communicating with the inlet 3 and the outlet 9 of the stator l, and including a partition 24 extending to about the center portions of the heat exch'angers 10 so that air can be circulated as a secondary cooling medium through inlets 8 and 31, cavity 14, and outlets 32 and 9.
- the arrangement shown in Fig. 3 is similar,
- a means 27a is provided in the cavity 14a and has of heat exchangers 10.
- the end portion of the bolts are threaded into therotor, body as described with reference to Fig. 3.
- Thes-tatorfl consists of two halves which are connected to each other by means of flanges 35 and bolts 35. This construction is known, and not an object of the present invention.
- each row of rotor blades 11, the conduit means 10 associated with therespective row of rotor blades IT, and the heat exchanger 10 secured to the respective conduit means it), constitute a detachable unit which is held by root members 21 and 23 in slot portions 25a of slots 25, and in grooves 29, respectively, in such a manner that each unit is axially slidable, but secured by the projecting means 25 against radial movement. Consequently, each unit can be removed in axial direction, and also mounted in axial direction independently of the other units.
- the opened cavities 14 and 14a are easily accessible so that each unit can be pulled out independently of the other units.
- each conduit means 10 and more particularly the respective associated heat exchangers 10 are all mounted in the same cavity of the rotor body, it is possible to cool all units simultaneously by a common secondary cooling medium which i circulated through inlets 31 or 8, outlets 32 or 9, and the respective cavity 14 of 14a in the rotor body.
- a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof and with a cavity adapted to receive a secondary cooling medium; a plurality of detachable units, eachunit mounted in one of said slots slidable in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including a row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, and a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the associated row of rotor blades so as to permit circulation of a coolant through said conduit means and the rotor blades of the respective unit independently of the other units, a part of said conduit means of each of said detachable units being located in said cavity so as to be cooled
- a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof and with a cavity adapted to receive a secondary cooling medium; a plurality of detachable units, each unit mounted in one of said slots slidable in axial direction so as to'permit removal and mounting of each unit in axial direction independently of the other units, each unit including a row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the associated row of rotor blades, and a heat exchanger communicating with said conduit means so as to permit circulation of a coolant through said heat exchanger, said conduit means and the rotor blades of the respective unit independently of the other units, said heat exchangers of said det
- an elongated rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof, and with a cavity located at one end of said rotor body and adapted to receive a secondary cooling medium
- a plurality of detachable units each unit mounted in one of said slots and slidable in axial direction so as to permit removal and mounting of eachunit in axial direction independently of the other units, each unit including a row of axially spaced rotor blades mounted in the associated slot formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage mean in the associated row of rotor blades, and a heat exchanger spaced in axial direction from said rotor blades and communicating with said conduit means so as to permit circulation of a coolant through said
- a rotor body having an axis and being formed with a cavity; a plurality of detachable units, each unit being mounted on said rotor body slidable in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, and a conduit means secured to said rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades so as to permit circulation of the coolant through said conduit means and through said passage means in the rotor blades of the respective unit independently of the other units, a part of the conduit means of each of said units being located in said cavity in said rotor body; and means for circulating a secondary cooling medium in said cavity about said part of the conduit means of each unit for cooling
- a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof and with a cavity; a plurality of detachable units, each unit mounted in one of said slots slidablc in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades, a heat exchanger secured to the respective conduit means and communicating with said conduit means; and means for circulating a secondary cooling medium in said cavity about said heat exchangers of all said detachable units.
- a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof and with a cavity; a plurality of detachable units, each unit mounted in one of said slots slidablc in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means sccured to the rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades, a heat exchanger secured to the respective conduit means and communicating with said conduit means, said heat exchangers being spaced in axial direction from said rotor blades; and means for circulating a secondary cooling medium in said cavity about
- a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof, and with a cavity adjacent one end of said rotor body; a plurality of detachable units, each unit mounted in one of said slots slidable in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades, a heat exchanger located in said cavity and being secured to the respective conduit means and communicating with said conduit means; and cooling means for circulating a secondary cooling medium through said heat exchangers of all said det
- a rotor body having an axis and being formed with a plurality of slots extending in axial direction ofsaid rotor body in the outer surface thereof, and with a cavity located spaced in axial direction from said rotor blades and adjacent one end of said rotor body; a plurality of detachable units, each unit mounted in one of said slots slidable in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades, a heat exchanger located in said cavity and being secured to the respective conduit means and communicating with said conduit means; and
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Feb. 19, 195 7 LEDlNFGd 2,782,000
GAS-TURBINE Filed DEC. 29, 1951 INVEN'I'OR; MAX VLEDINEGG United States Patent GAS-TURBINE Max Ledinegg, Vienna, Austria, assignor toSimrnering- Graz-Pauker Aktiengesellschaft fiir Maschinem, Kesselund Waggonbau, Vienna, Austria, a company of Austria The invention relates to a device for cooling the blades in gas turbines. The cooling is intended primarily for blades subjected to high temperature stressing beyond 700 C. and is effected in a manner known per se by an evaporating liquid, which is caused to circulate by the action of centrifugal force by means of longitudinal bores in the blade.
It is known to associate a common cooling system with all blades. It is also known to associate with each blade a cooler of its own, which is independent of the others and in which the condensation of the vapor formed in the blade is effected. Thereby it is prevented that the whole cooling liquid may flow out upon the leakage of the cooling system even of one blade only, which would result in extensive damage by all blades becoming red hot. On the contrary, the damage is re stricted to the one blade concerned. The coolers themselves may'be cooled by a secondary medium, water or air. Particularly in the case of cooling by air, large passage cross sections must be provided in the rotor, whereby the construction of the whole turbine is rendered more difficult in particular by the requirement oflarge rotor diameters.
The further development of the invention consists in that each axial row of blades has associated therewith a heat exchanger, which i independent of the heat exchangers of the other rows of blades- Consequently axial rows of blades can be removed easily together with the heat exchanger. The association of a heat exchanger with an axial row of blades, however, enables also a special construction, which in accordance with the invention consists in that the heat exchanger associated with each row of blades are axially spaced from the blade rings. Therefore it is no longer necessary to conduct the secondary cooling medium axially through the rotor; on the contrary, that medium may be reversed within or behind the sets of coolers so as to emerge at the same end olthe rotor body where his admitted.
In-the accompanying drawings; I
Fig. 1 shows by way of example an embodiment of the invention in an axial section taken through the upper'half thereof, in the case of air being used as a secondary cooling medium,
"Fig. 2 is a fragmentary transverse sectional view illustrating a system of detachable units according to the present invention on an enlargedscale,
Fig. 3 shows the arrangement in the case of a liquid secondary cooling medium, particularly water, being used.
In Fig. 1, 1 is the casing of the turbine with the guide blades 5, 2 is the rotor with the rotor blades 11. The hot gases enter at 3 the blade ring formed by the guide and rotor blades, and pass off at 4.
The rotating part is sealed against the casing by the labyrinth packings 29. In order to be cooled each rotor blade has passage means including central bores 13-and a larger number of peripheral bores 12, which communicate witheacb other at the blade top. In the cen- Cir 7 2,782,000 Patented Feb. 19, 1957 tral bores the cooler cooling medium, of higher specific gravity, flows outwardly under centrifugal force, i heated or evaporated, and when its specific gravity has thus been reduced the medium is forced inwardly. This cooling cycle does not form part of the invention but has been described only by way of examplebecause other cooling processes may be used without departing from the scope of the invention.
' The attachment of the rotor blades to the rotor body is effected by means of fir-cone roots 21 engaging the outer slot portions 25a of slots 25 in the rotor body. Projecting means 25 in the slot portions 25a secure the rotor blades against radial movement. A conduit means It? is secured to the roots of all rotor blades of each axial row of rotor blades, and is located in the inner slot portion 25b of the respective slot 25. Each conduit means it) communicates with the passages 12, 13 in the rotor blades of the respective row, and with the passage of a heat exchanger 10 which is secured to the tubes having cooling fins and being inserted with the undercut roots 23 thereof into corresponding axially extending grooves 29 which are formed in the cavity 14 of the rotor body.
The cavity 14 shown in Fig. l is closed by a means 27 provided with an inlet 31 and an outlet 32, respec tively communicating with the inlet 3 and the outlet 9 of the stator l, and including a partition 24 extending to about the center portions of the heat exch'angers 10 so that air can be circulated as a secondary cooling medium through inlets 8 and 31, cavity 14, and outlets 32 and 9. The arrangement shown in Fig. 3 is similar,
' and a means 27a is provided in the cavity 14a and has of heat exchangers 10. The end portion of the bolts are threaded into therotor, body as described with reference to Fig. 3.
Thes-tatorfl consists of two halves which are connected to each other by means of flanges 35 and bolts 35. This construction is known, and not an object of the present invention.
It will be understood that each row of rotor blades 11, the conduit means 10 associated with therespective row of rotor blades IT, and the heat exchanger 10 secured to the respective conduit means it), constitute a detachable unit which is held by root members 21 and 23 in slot portions 25a of slots 25, and in grooves 29, respectively, in such a manner that each unit is axially slidable, but secured by the projecting means 25 against radial movement. Consequently, each unit can be removed in axial direction, and also mounted in axial direction independently of the other units.
In. order to remove, or mount, a unit, it is, of course, necessary to first detach the respectivestator half, and
to withdraw the means 27 or 27a after removing the 3 bolts 28. The opened cavities 14 and 14a are easily accessible so that each unit can be pulled out independently of the other units.
Due to the fact that part of each conduit means 10, and more particularly the respective associated heat exchangers 10 are all mounted in the same cavity of the rotor body, it is possible to cool all units simultaneously by a common secondary cooling medium which i circulated through inlets 31 or 8, outlets 32 or 9, and the respective cavity 14 of 14a in the rotor body.
I claim:
1. In a gas turbine rotor, in combination, a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof and with a cavity adapted to receive a secondary cooling medium; a plurality of detachable units, eachunit mounted in one of said slots slidable in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including a row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, and a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the associated row of rotor blades so as to permit circulation of a coolant through said conduit means and the rotor blades of the respective unit independently of the other units, a part of said conduit means of each of said detachable units being located in said cavity so as to be cooled by said secondary cooling medium.
2. In a gas turbine rotor, in combination, a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof and with a cavity adapted to receive a secondary cooling medium; a plurality of detachable units, each unit mounted in one of said slots slidable in axial direction so as to'permit removal and mounting of each unit in axial direction independently of the other units, each unit including a row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the associated row of rotor blades, and a heat exchanger communicating with said conduit means so as to permit circulation of a coolant through said heat exchanger, said conduit means and the rotor blades of the respective unit independently of the other units, said heat exchangers of said detachable units being located in said cavity so as to be cooled by said secondary cooling medium.
3. In a gas turbine rotor, in combination, an elongated rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof, and with a cavity located at one end of said rotor body and adapted to receive a secondary cooling medium, a plurality of detachable units, each unit mounted in one of said slots and slidable in axial direction so as to permit removal and mounting of eachunit in axial direction independently of the other units, each unit including a row of axially spaced rotor blades mounted in the associated slot formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage mean in the associated row of rotor blades, and a heat exchanger spaced in axial direction from said rotor blades and communicating with said conduit means so as to permit circulation of a coolant through said heat exchanger, said conduit means and the rotor blades of the respective unit independently of the other units, said heat exchangers of said detachable units 1 4 being located in said cavity so as to be cooled by said secondary cooling medium.
4. In a gas turbine rotor, in combination, a rotor body having an axis and being formed with a cavity; a plurality of detachable units, each unit being mounted on said rotor body slidable in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, and a conduit means secured to said rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades so as to permit circulation of the coolant through said conduit means and through said passage means in the rotor blades of the respective unit independently of the other units, a part of the conduit means of each of said units being located in said cavity in said rotor body; and means for circulating a secondary cooling medium in said cavity about said part of the conduit means of each unit for cooling said conduit means of all said detachable units.
5. In a gas turbine rotor, in combination, a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof and with a cavity; a plurality of detachable units, each unit mounted in one of said slots slidablc in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades, a heat exchanger secured to the respective conduit means and communicating with said conduit means; and means for circulating a secondary cooling medium in said cavity about said heat exchangers of all said detachable units.
6. In a gas turbine rotor, in combination, a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof and with a cavity; a plurality of detachable units, each unit mounted in one of said slots slidablc in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means sccured to the rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades, a heat exchanger secured to the respective conduit means and communicating with said conduit means, said heat exchangers being spaced in axial direction from said rotor blades; and means for circulating a secondary cooling medium in said cavity about said heat exchangers of all'of said detachable units.
7. In a gas turbine rotor, in combination, a rotor body having an axis and being formed with a plurality of slots extending in axial direction of said rotor body in the outer surface thereof, and with a cavity adjacent one end of said rotor body; a plurality of detachable units, each unit mounted in one of said slots slidable in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades, a heat exchanger located in said cavity and being secured to the respective conduit means and communicating with said conduit means; and cooling means for circulating a secondary cooling medium through said heat exchangers of all said detachable units and including an axially extending partition located in said cavity so as to define in said cavity an inlet and an outlet for guiding said secondary cooling medium in one axial direction into said cavity and in the opposite axial direction out of said cavity so that said secondary cooling medium is supplied to and discharged from the same side of said heat exchangers.
8. In a gas turbine rotor; in combination, a rotor body having an axis and being formed with a plurality of slots extending in axial direction ofsaid rotor body in the outer surface thereof, and with a cavity located spaced in axial direction from said rotor blades and adjacent one end of said rotor body; a plurality of detachable units, each unit mounted in one of said slots slidable in axial direction so as to permit removal and mounting of each unit in axial direction independently of the other units, each unit including an axially extending row of axially spaced rotor blades formed with passage means for a coolant, means securing the respective unit to said rotor body against radial movement, a conduit means secured to the rotor blades of said row of rotor blades and communicating with said passage means in the rotor blades of the associated row of rotor blades, a heat exchanger located in said cavity and being secured to the respective conduit means and communicating with said conduit means; and
cooling means for circulating a secondary cooling me- References Cited in the file of this patent UNITED STATES PATENTS 2,369,795 Planiol et al Feb. 20, 1945 FOREIGN PATENTS 229,933 Switzerland Feb. 16, 1944 271,742 Switzerland Nov. 15, 1950 610,737 Great Britain Oct. 20, 1948 623,841 Great Britain May 24, 1949
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AT711741X | 1951-05-28 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2782000A true US2782000A (en) | 1957-02-19 |
Family
ID=3679674
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US264120A Expired - Lifetime US2782000A (en) | 1951-05-28 | 1951-12-29 | Gas-turbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US2782000A (en) |
| CH (1) | CH301140A (en) |
| DE (1) | DE941100C (en) |
| GB (1) | GB711741A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2947512A (en) * | 1956-12-19 | 1960-08-02 | Int Harvester Co | Turbine blade and nozzle blade cooling construction for gas turbines |
| US2952441A (en) * | 1956-12-10 | 1960-09-13 | Int Harvester Co | Cooling construction for gas turbine blades |
| US3765480A (en) * | 1970-04-24 | 1973-10-16 | Siemens Ag | Device for cooling rotors |
| US4136516A (en) * | 1977-06-03 | 1979-01-30 | General Electric Company | Gas turbine with secondary cooling means |
| US4190398A (en) * | 1977-06-03 | 1980-02-26 | General Electric Company | Gas turbine engine and means for cooling same |
| US5151012A (en) * | 1981-03-20 | 1992-09-29 | Rolls-Royce Plc | Liquid cooled aerofoil blade |
| US5201634A (en) * | 1981-04-28 | 1993-04-13 | Rolls-Royce Plc | Cooled aerofoil blade |
| US5782076A (en) * | 1996-05-17 | 1998-07-21 | Westinghouse Electric Corporation | Closed loop air cooling system for combustion turbines |
| US20180216473A1 (en) * | 2017-01-31 | 2018-08-02 | United Technologies Corporation | Hybrid airfoil cooling |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1186274B (en) * | 1960-01-20 | 1965-01-28 | Siemens Ag | Gas turbine system with internal evaporation cooling of the gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH229933A (en) * | 1941-09-05 | 1943-11-30 | Messerschmitt Boelkow Blohm | Device for cooling turbine blades by liquid evaporation. |
| US2369795A (en) * | 1941-11-17 | 1945-02-20 | Andre P E Planiol | Gaseous fluid turbine or the like |
| GB610737A (en) * | 1946-03-19 | 1948-10-20 | Power Jets Res & Dev Ltd | Improvements relating to turbine and like blading |
| GB623841A (en) * | 1947-05-16 | 1949-05-24 | Power Jets Res & Dev Ltd | Improvements in or relating to turbine and like rotors |
| CH271742A (en) * | 1948-11-26 | 1950-11-15 | Simmering Graz Pauker Ag | Gas turbine with liquid-cooled rotor blades. |
-
1951
- 1951-12-28 CH CH301140D patent/CH301140A/en unknown
- 1951-12-29 US US264120A patent/US2782000A/en not_active Expired - Lifetime
- 1951-12-30 DE DES26608A patent/DE941100C/en not_active Expired
- 1951-12-31 GB GB30433/51A patent/GB711741A/en not_active Expired
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH229933A (en) * | 1941-09-05 | 1943-11-30 | Messerschmitt Boelkow Blohm | Device for cooling turbine blades by liquid evaporation. |
| US2369795A (en) * | 1941-11-17 | 1945-02-20 | Andre P E Planiol | Gaseous fluid turbine or the like |
| GB610737A (en) * | 1946-03-19 | 1948-10-20 | Power Jets Res & Dev Ltd | Improvements relating to turbine and like blading |
| GB623841A (en) * | 1947-05-16 | 1949-05-24 | Power Jets Res & Dev Ltd | Improvements in or relating to turbine and like rotors |
| CH271742A (en) * | 1948-11-26 | 1950-11-15 | Simmering Graz Pauker Ag | Gas turbine with liquid-cooled rotor blades. |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2952441A (en) * | 1956-12-10 | 1960-09-13 | Int Harvester Co | Cooling construction for gas turbine blades |
| US2947512A (en) * | 1956-12-19 | 1960-08-02 | Int Harvester Co | Turbine blade and nozzle blade cooling construction for gas turbines |
| US3765480A (en) * | 1970-04-24 | 1973-10-16 | Siemens Ag | Device for cooling rotors |
| US4136516A (en) * | 1977-06-03 | 1979-01-30 | General Electric Company | Gas turbine with secondary cooling means |
| US4190398A (en) * | 1977-06-03 | 1980-02-26 | General Electric Company | Gas turbine engine and means for cooling same |
| US5151012A (en) * | 1981-03-20 | 1992-09-29 | Rolls-Royce Plc | Liquid cooled aerofoil blade |
| US5201634A (en) * | 1981-04-28 | 1993-04-13 | Rolls-Royce Plc | Cooled aerofoil blade |
| US5782076A (en) * | 1996-05-17 | 1998-07-21 | Westinghouse Electric Corporation | Closed loop air cooling system for combustion turbines |
| US20180216473A1 (en) * | 2017-01-31 | 2018-08-02 | United Technologies Corporation | Hybrid airfoil cooling |
| US10428660B2 (en) * | 2017-01-31 | 2019-10-01 | United Technologies Corporation | Hybrid airfoil cooling |
Also Published As
| Publication number | Publication date |
|---|---|
| DE941100C (en) | 1956-04-05 |
| CH301140A (en) | 1954-08-31 |
| GB711741A (en) | 1954-07-07 |
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