Turbine nozzle with integral impingement blanket
a technology of impingement blanket and turbine nozzle, which is applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of reducing the cooling efficiency of the turbine nozzle, bleed flows representing a loss of net work output and/or thrust to the thermodynamic cycle, and flow is susceptible to leakag
Inactive Publication Date: 2009-09-03
GENERAL ELECTRIC CO
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[0006]According to one aspect of the invention, a turbine nozzle segment includes: (a) an arcuate outer band segment; (b) a hollow, airfoil-shaped turbine vane extending radially inward from the outer band segment; (c) a manifold cover secured to the outer band such that the manifold cover and the outer band segment cooperatively define an impingement cavity; and (d) an impingement blanket disposed in the impingement cavity, the impingement blanket having at least one impingement hole formed therethrough which is arranged to direct cooling air at the outer band segment.
[0007]According to another aspect of the invention, a turbine nozzle assembly for a gas turbine engine includes: (a) a plurality of turbine nozzle segments arranged in an annular array, each turbine nozzle segment having: (i) an arcuate outer band segment; (ii) a hollow, airfoil-shaped turbine vane extending radially inwardly from the outer band segment; (iii) a manifold cover secured to the outer band such that the manifold cover and the outer band segment cooperatively define an impingement cavity; and (iv) an i
Problems solved by technology
These bleed flows represent a loss of net work output and / or thrust to the thermodynamic cycle.
The second configuration utilizes a separate impingement ring to cool the outer band, but this flow is susceptible to leakage through the gaps between adjacent nozzle segments.
In either case, the turbine nozzle cooling is less efficient than desired.
Method used
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[0015]Referring to the drawings wherein identical reference numerals denote the same elements throughout the various views, FIG. 1 depicts a portion of a gas generator turbine 10, which is part of a gas turbine engine of a known type. The function of the gas generator turbine 10 is to extract energy from high-temperature, pressurized combustion gases from an upstream combustor (not shown) and to convert the energy to mechanical work, in a known manner. The gas generator turbine 10 drives an upstream compressor (not shown) through a shaft so as to supply pressurized air to the combustor.
[0016]In the illustrated example, the engine is a turboshaft engine and a work turbine would be located downstream of the gas generator turbine 10 and coupled to an output shaft. However, the principles described herein are equally applicable to turboprop, turbojet, and turbofan engines, as well as turbine engines used for other vehicles or in stationary applications.
[0017]The gas generator turbine 10...
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A turbine nozzle segment includes: (a) an arcuate outer band segment; (b) a hollow, airfoil-shaped turbine vane extending radially inward from the outer band segment; (c) a manifold cover secured to the outer band such that the manifold cover and the outer band segment cooperatively define an impingement cavity; and (d) an impingement blanket disposed in the impingement cavity, the impingement blanket having at least one impingement hole formed therethrough which is arranged to direct cooling air at the outer band segment. A method is provided for impingement cooling the outer band segment.
Description
BACKGROUND OF THE INVENTION[0001]This invention relates generally to gas turbine engine turbines and more particularly to methods for cooling turbine sections of such engines.[0002]A gas turbine engine includes a turbomachinery core having a high pressure compressor, combustor, and high pressure or gas generator turbine in serial flow relationship. The core is operable in a known manner to generate a primary gas flow. In a turbojet or turbofan engine, the core exhaust gas is directed through a nozzle to generate thrust. A turboshaft engine uses a low pressure or “work” turbine downstream of the core to extract energy from the primary flow to drive a shaft or other mechanical load.[0003]The gas generator turbine includes annular arrays (“rows”) of stationary vanes or nozzles that direct the gases exiting the combustor into rotating blades or buckets. Collectively one row of nozzles and one row of blades make up a “stage”. Typically two or more stages are used in serial flow relations...
Claims
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Login to View More IPC IPC(8): F01D25/12
CPCF01D9/042F01D25/12F05D2260/201F01D25/246F05D2240/81F01D25/14
Inventor SHAPIRO, JASON DAVIDFLODMAN, DAVID ALLEN
Owner GENERAL ELECTRIC CO