Methods and apparatus for cooling gas turbine nozzles
a gas turbine engine and cooling technology, applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of shortening the useful life of the nozzle, nozzles subjected to high temperatures, and may be subjected to high mechanical loads, so as to facilitate the cooling of metal temperatures
Inactive Publication Date: 2009-03-10
GENERAL ELECTRIC CO
View PDF16 Cites 32 Cited by
- Summary
- Abstract
- Description
- Claims
- Application Information
AI Technical Summary
Benefits of technology
"The invention provides a method for assembling a turbine nozzle for a gas turbine engine by integrating a leading airfoil and a trailing airfoil with a platform. An insert is inserted into at least one of the airfoil vanes, which includes cooling openings to direct cooling air towards the vane's sidewalls. The cooling air helps to lower metal temperatures and improve the engine's performance. The technical effects include improved cooling efficiency and reduced metal temperatures in the turbine nozzle."
Problems solved by technology
In addition, because such turbine nozzles are subjected to high temperatures and may be subjected to high mechanical loads, at least some known doublets include an identical insert installed within each airfoil vane cavity to distribute cooling air supplied internally to each airfoil vane.
However, because of the construction of the doublet, mechanical loads and thermal stresses may still be induced unequally across the turbine nozzle.
Over time, continued operation with an unequal distribution of stresses within the nozzle may shorten a useful life of the nozzle.
Method used
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View moreImage
Smart Image Click on the blue labels to locate them in the text.
Smart ImageViewing Examples
Examples
Experimental program
Comparison scheme
Effect test
Embodiment Construction
[0011]FIG. 1 is a schematic illustration of a gas turbine engine 10 including a fan assembly 12, a high-pressure compressor 14, and a combustor 16. Engine 10 also includes a high-pressure turbine 18 and a low-pressure turbine 20. Engine 10 has an intake, or upstream, side 28 and an exhaust, or downstream, side 30. In one embodiment, engine 10 is a CF6-80 engine commercially available from General Electric Aircraft Engines, Cincinnati, Ohio.
[0012]In operation, air flows through fan assembly 12 and compressed air is supplied to high-pressure compressor 14. The highly compressed air is delivered to combustor 16. Airflow from combustor 16 is discharged through a turbine nozzle assembly (not shown in FIG. 1) that includes a plurality of nozzles (not shown in FIG. 1) and used to drive turbines 18 and 20. Turbine 20, in turn, drives fan assembly 12, and turbine 18 drives high-pressure compressor 14.
[0013]FIG. 2 is an exploded perspective forward-looking-aft view of turbine nozzle 50 that m...
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More PUM
Login to View More Abstract
A method for assembling a turbine nozzle for a gas turbine engine facilitates improving cooling efficiency of the turbine nozzle. The method includes providing a hollow doublet including a leading airfoil and a trailing airfoil coupled by at least one platform, wherein each airfoil includes a first sidewall and a second sidewall that extend between a respective leading and trailing edge. The method also includes inserting an insert into at least one of the airfoils, wherein the insert includes a first sidewall including a first plurality of cooling openings that extending therethrough, and a second sidewall including a second plurality of cooling openings extending therethrough, and wherein the first plurality of cooling openings facilitate more cooling of the airfoil than the second plurality of cooling openings.
Description
BACKGROUND OF THE INVENTION[0001]This invention relates generally to gas turbine engine nozzles and more particularly, to methods and apparatus for cooling gas turbine engine nozzles.[0002]Gas turbine engines include combustors which ignite fuel-air mixtures which are then channeled through a turbine nozzle assembly towards a turbine. At lease some known turbine nozzle assemblies include a plurality of nozzles arranged circumferentially and configured as doublets. A turbine nozzle doublet includes a pair of circumferentially-spaced hollow airfoil vanes coupled by integrally-formed inner and outer band platforms.[0003]The doublet type turbine nozzles facilitate improving durability and reducing leakage in comparison to non-doublet turbine nozzles. Furthermore, turbine nozzle doublets also facilitate reducing manufacturing and assembly costs. In addition, because such turbine nozzles are subjected to high temperatures and may be subjected to high mechanical loads, at least some known ...
Claims
the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More Application Information
Patent Timeline
Login to View More Patent Type & Authority Patents(United States)
IPC IPC(8): F01D9/06F01D5/18F01D9/02F01D25/12F02C7/18
CPCF01D5/189F01D9/02F01D25/12F05D2260/201Y02T50/60
Inventor POWIS, ANDREW CHARLESCLARKE, JONATHAN PHILIPTRESSLER, JUDD DODGE
Owner GENERAL ELECTRIC CO