US3561882A - Turbine blade cooling - Google Patents
Turbine blade cooling Download PDFInfo
- Publication number
- US3561882A US3561882A US298947A US29894752A US3561882A US 3561882 A US3561882 A US 3561882A US 298947 A US298947 A US 298947A US 29894752 A US29894752 A US 29894752A US 3561882 A US3561882 A US 3561882A
- Authority
- US
- United States
- Prior art keywords
- blades
- nozzle
- passages
- liquid
- tail portion
- 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
Links
Images
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
- F01D5/185—Liquid cooling
Definitions
- This invention relates to turbines, more particularly to the cooling of turbine blades by insulation with, and vaporization of, liquid sprayed thereon, and has for an object to provide improved blade structure for this type of cooling.
- the nozzle blades have longitudinal passages in the tail portions thereof, and ports therefrom distributed along the tail portions provide for spraying of liquid into the nozzle passages. With this arrangement, the entire crosssection of each nozzle blade will be reduced in temperature by conduction of heat to the liquid passing through the tail portion passage.
- the nozzle blades are not subject to centrifugal stress, such blades can be subjected to full gas temperature.
- the nozzle blades are each hollowed out between the inlet edge and the tail portion to leave an insulating air gap to reduce the conduction of heat to the Water passing through the tail portion passage, and the heat loss to the nozzle blade will thereby be reduced considerably; and, in this connection, the heat loss may be even further reduced if the hollowed-out portion is filled with ceramic material.
- the present invention has for its object to improve direct liquid cooling of the blades by having the nozzle blades, from which liquid is sprayed for this purpose, hollowed out between the inlet edges and the tail portions and to fill the hollowed-out portions with ceramic material to reduce the heat loss from such blades to the liquid traversing the passages in order that the liquid may be more effective for spray-cooling of the moving blades.
- FIG. 1 is a fragmentary View of a pair of rows of gas turbine nozzles and moving blades
- FIG. 2 is a fragmentary sectional view, taken along the line IIII of FIG. 1, looking in the direction indicated by the arrows, showing liquid supplied to the nozzle blades.
- Each nozzle blade has a rounded inlet edge 14 and convex and concave faces 15 and 16, which converge to define the tail portion 17.
- Each tail portion 17 has a longitudinal passage 18 formed therein, supplied with water or other suitable liquid, and from which water is sprayed into the adjacent 3,561,882 Patented Feb. 9, 1971 nozzle passages by ports 19 distributed along the tail portions.
- the sprayed water is carried along with the motive fluid traversing the nozzle passages for impingement upon the moving blades 12 to cool the latter by 5 evaporation and by insulation.
- each of the nozzle blades is hollowed out at 20, thereby reducing the heat conductive section of the blade between the inlet edge and the tail portion passage. While such hollowing out reduces the heat loss to the water traversing the passage, this action may be made even more effective by filling the hollowed-out portion with ceramic material 21.
- the cylinder 22 carrying the nozzle blades may have annular chambers 24 supplied with liquid by a conduit 25. As the passages 18 of the nozzle blades continue through the roots thereof and communicate with the annular chambers, provision is thereby made for adequate liquid flow through the passages.
- a row of nOZZle blades followed by a row of moving blades the tail portions of the nozzle blades having longitudinal passages formed therein, adapted to be supplied with liquid and having ports through which liquid may sprayed into the nozzle passages from the tail portion passages; and each of said nozzle blades being hollow between the inlet edge thereof and the tail portion to reduce the heat conductive area between the inlet edge and the tail portion.
- each of said nozzle blades having an inlet edge portion and a tail portion, said tail portion having passages formed therein adapted to be supplied with liquid and having ports through which the liquid may be ejected into the nozzle passages from the tail portion passages; each of said nozzle blades having a hollow portion between said inlet edge portion and said tail portion to reduce the heat conductive area between said inlet edge portion and said tail portion, and a mass of insulating material disposed in said hollow portion.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1. THE GAS TURBINE BLADE COOLING, A ROW OF NOZZLE BLADES FOLLOWED BY A ROW OF MOVING BLADES, THE TAIL PORTIONS OF THE NOZZLE BLADES HAVING LONGTUDINAL PASSAGES THROUGH THEREIN, ADAPTED TO BE SUPPLIED WITH LIQUID AND HAVING PORTS THROUGH WHICH LIQUID MAY SPRAYED INTO THE NOZZLE PASSAGES FROM THE TAIL PORTION PASSAGES, AND EACH OF SAID NOZZLE BLADES BEING HOLLOW BETWEEN THE INLET EDGE THEREOF AND THE TAIL PORTION TO REDUCE THE HEAT CONDUCTIVE AREA BETWEEN THE INLET EDGE AND THE TAIL PORTION.
Description
Feb. 9, 1971 E SQMERS lETAL 3,561,882
TURBINE BLADE COOLING Filed July 15, 1952 FIG. I.
WITNESSES:
l2 INVENTDR EDWARD v. SOMERS EDWARD BURKE United States Patent ()flice US. Cl. 415-115 3 Claims This invention relates to turbines, more particularly to the cooling of turbine blades by insulation with, and vaporization of, liquid sprayed thereon, and has for an object to provide improved blade structure for this type of cooling.
It has previously been proposed to cool turbine blades by spraying liquid thereonto from the tail portions of the nozzle blades upstream thereof, the liquid being carried along with the turbine motive fluid for impingement upon the following row or rows of rotor and stator blades to cool the latter by vaporization and by partially insulating them from the hot gas stream.
The nozzle blades have longitudinal passages in the tail portions thereof, and ports therefrom distributed along the tail portions provide for spraying of liquid into the nozzle passages. With this arrangement, the entire crosssection of each nozzle blade will be reduced in temperature by conduction of heat to the liquid passing through the tail portion passage.
Since the nozzle blades are not subject to centrifugal stress, such blades can be subjected to full gas temperature. In accordance with the present invention, therefore, the nozzle blades are each hollowed out between the inlet edge and the tail portion to leave an insulating air gap to reduce the conduction of heat to the Water passing through the tail portion passage, and the heat loss to the nozzle blade will thereby be reduced considerably; and, in this connection, the heat loss may be even further reduced if the hollowed-out portion is filled with ceramic material. Therefore, the present invention has for its object to improve direct liquid cooling of the blades by having the nozzle blades, from which liquid is sprayed for this purpose, hollowed out between the inlet edges and the tail portions and to fill the hollowed-out portions with ceramic material to reduce the heat loss from such blades to the liquid traversing the passages in order that the liquid may be more effective for spray-cooling of the moving blades.
The foregoing and other objects are effected by the invention as will be apparent from the following description taken in connection with the accompanying drawing, forming a part of this application, in which:
FIG. 1 is a fragmentary View of a pair of rows of gas turbine nozzles and moving blades; and
FIG. 2 is a fragmentary sectional view, taken along the line IIII of FIG. 1, looking in the direction indicated by the arrows, showing liquid supplied to the nozzle blades.
In the drawing, there is shown a turbine row of nozzle blades defining nozzle passages 11 and followed by a moving row of blades 12.
Each nozzle blade has a rounded inlet edge 14 and convex and concave faces 15 and 16, which converge to define the tail portion 17.
Each tail portion 17 has a longitudinal passage 18 formed therein, supplied with water or other suitable liquid, and from which water is sprayed into the adjacent 3,561,882 Patented Feb. 9, 1971 nozzle passages by ports 19 distributed along the tail portions. The sprayed water is carried along with the motive fluid traversing the nozzle passages for impingement upon the moving blades 12 to cool the latter by 5 evaporation and by insulation.
To secure more effective cooling of the moving blades, each of the nozzle blades is hollowed out at 20, thereby reducing the heat conductive section of the blade between the inlet edge and the tail portion passage. While such hollowing out reduces the heat loss to the water traversing the passage, this action may be made even more effective by filling the hollowed-out portion with ceramic material 21.
Any suitable means may be used to assure of the nozzle blade passages being supplied with liquid. For example, the cylinder 22 carrying the nozzle blades may have annular chambers 24 supplied with liquid by a conduit 25. As the passages 18 of the nozzle blades continue through the roots thereof and communicate with the annular chambers, provision is thereby made for adequate liquid flow through the passages.
While the invention has been shown in but one form, it will be obvious to those skilled in the art that it is not so limited, but is susceptible of various changes and 25 modifications Without departing from the spirit thereof.
What is claimed is:
1. In gas turbine blade cooling, a row of nOZZle blades followed by a row of moving blades; the tail portions of the nozzle blades having longitudinal passages formed therein, adapted to be supplied with liquid and having ports through which liquid may sprayed into the nozzle passages from the tail portion passages; and each of said nozzle blades being hollow between the inlet edge thereof and the tail portion to reduce the heat conductive area between the inlet edge and the tail portion.
2. The combination as claimed in claim 1 wherein the hollows of the nozzle blades are filled with ceramic material.
3. In gas turbine blade cooling, a row of nozzle blades followed by a row of moving blades; each of said nozzle blades having an inlet edge portion and a tail portion, said tail portion having passages formed therein adapted to be supplied with liquid and having ports through which the liquid may be ejected into the nozzle passages from the tail portion passages; each of said nozzle blades having a hollow portion between said inlet edge portion and said tail portion to reduce the heat conductive area between said inlet edge portion and said tail portion, and a mass of insulating material disposed in said hollow portion.
References Cited UNITED STATES PATENTS 2,625,013 1/1953 Howard et al 39.66X 2,625,793 1/1953 Mierley et al. 6039.66X 2,149,510 3/1939 Darrieus 25339.1B 2,647,368 8/1953 Triebbnigg et al. 25339.1B
6O FOREIGN PATENTS 498,572 2/1951 Belgium 25339.1B
SAMUEL FEINBERG, Primary Examiner US. Cl. X.R.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US298947A US3561882A (en) | 1952-07-15 | 1952-07-15 | Turbine blade cooling |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US298947A US3561882A (en) | 1952-07-15 | 1952-07-15 | Turbine blade cooling |
Publications (1)
Publication Number | Publication Date |
---|---|
US3561882A true US3561882A (en) | 1971-02-09 |
Family
ID=23152682
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US298947A Expired - Lifetime US3561882A (en) | 1952-07-15 | 1952-07-15 | Turbine blade cooling |
Country Status (1)
Country | Link |
---|---|
US (1) | US3561882A (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3694102A (en) * | 1969-07-26 | 1972-09-26 | Daimler Benz Ag | Guide blades of axial compressors |
US3726604A (en) * | 1971-10-13 | 1973-04-10 | Gen Motors Corp | Cooled jet flap vane |
US4111596A (en) * | 1977-01-10 | 1978-09-05 | The United States Of America As Represented By The Secretary Of The Navy | Turbine blade cooling system |
EP1302639A3 (en) * | 2001-10-11 | 2007-09-26 | General Electric Company | A method for enhancing part life in a gas stream |
EP3059391A1 (en) * | 2015-02-18 | 2016-08-24 | United Technologies Corporation | Gas turbine engine turbine blade cooling using upstream stator vane |
-
1952
- 1952-07-15 US US298947A patent/US3561882A/en not_active Expired - Lifetime
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3694102A (en) * | 1969-07-26 | 1972-09-26 | Daimler Benz Ag | Guide blades of axial compressors |
US3726604A (en) * | 1971-10-13 | 1973-04-10 | Gen Motors Corp | Cooled jet flap vane |
US4111596A (en) * | 1977-01-10 | 1978-09-05 | The United States Of America As Represented By The Secretary Of The Navy | Turbine blade cooling system |
EP1302639A3 (en) * | 2001-10-11 | 2007-09-26 | General Electric Company | A method for enhancing part life in a gas stream |
EP3059391A1 (en) * | 2015-02-18 | 2016-08-24 | United Technologies Corporation | Gas turbine engine turbine blade cooling using upstream stator vane |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US3301526A (en) | Stacked-wafer turbine vane or blade | |
US3094310A (en) | Blades for fluid flow machines | |
US4040767A (en) | Coolable nozzle guide vane | |
US3446481A (en) | Liquid cooled turbine rotor | |
CA1131563A (en) | Film cooled airfoil body | |
US3017159A (en) | Hollow blade construction | |
US4183716A (en) | Air-cooled turbine blade | |
US3527543A (en) | Cooling of structural members particularly for gas turbine engines | |
US4105364A (en) | Vane for a gas turbine engine having means for impingement cooling thereof | |
US4013376A (en) | Coolable blade tip shroud | |
US8128366B2 (en) | Counter-vortex film cooling hole design | |
US3994622A (en) | Coolable turbine blade | |
US3700418A (en) | Cooled airfoil and method of making it | |
US5201847A (en) | Shroud design | |
US3844343A (en) | Impingement-convective cooling system | |
US3051439A (en) | Blades for gas turbine engines | |
US3111302A (en) | Blades for fluid flow machines | |
CA2042266A1 (en) | Curved film cooling holes for gas turbine engine vanes | |
US3561882A (en) | Turbine blade cooling | |
GB751011A (en) | Improvements in or relating to the cooling of turbine blades | |
JPS6056883B2 (en) | gas turbine moving blades | |
US3981609A (en) | Coolable blade tip shroud | |
JPS58197402A (en) | Gas turbine blade | |
GB651787A (en) | Improvements in or relating to blading for turbines and like machines | |
GB584580A (en) | Improvements in or relating to turbine blades |