Rotary kinetic fluid motors or pumps – With diversely oriented inlet or additional inlet for... – Diverse fluids to motor
Reexamination Certificate
1999-04-27
2001-05-08
Look, Edward K. (Department: 3745)
Rotary kinetic fluid motors or pumps
With diversely oriented inlet or additional inlet for...
Diverse fluids to motor
C416S09700R, C029S889200, C029S889220, C029S889721, C029S889722
Reexamination Certificate
active
06227801
ABSTRACT:
FIELD OF THE INVENTION
The present invention relates to turbine engines, and more particularly to turbine engines having improved high pressure turbine cooling.
BACKGROUND OF THE INVENTION
Turbine engines, such as those used as aircraft turbojets or turbofans typically include from front to rear, in the direction of fluid flow in the engine, fan, compressor, combustion and turbine sections within a housing. These sections include rotating components mounted on one or more coaxial shafts for rotation about a central axis of the engine.
The fan section draws air into the engine. It is compressed in the compressor section, and admixed with fuel in the combustion section where the mixture is ignited. Combustion gases exit the combustion section and drive one or more turbines within the turbine sections.
Typically a first stage, high pressure turbine (“HPT”) blade forming part of the initial turbine section, is cooled to prevent melting by using uncombusted high pressure air, referred to as P3 air. Specifically, the P3 air is passed through a tangential on-board injector (“TOBI”) nozzle. The TOBI nozzle reduces the relative total temperature of the P3 air typically by approximately 100° F. (55° C.). The reduced temperature P3 air is passed into a HPT disk/coverplate rotating cavity and over the HPT blade. There, the P3 air cools the HPT blade typically using showerhead cooling.
Use of high pressure P3 air, however, is thermodynamically inefficient. Moreover, a TOBI nozzle and ancillary components add weight to the engine. Similarly, showerhead cooling requires the machining of relatively complex components.
Accordingly, a more thermodynamically efficient method of cooling an HPT within a turbine engine is desirable. Moreover, an engine with reduced weight of components associated with HPT cooling is desirable.
SUMMARY OF THE INVENTION
Accordingly, it is an object of the present invention to provide a turbine engine, having improved HPT cooling.
In accordance with the present invention, relatively cool intermediate pressure air is diverted from a region of a compressor section within a turbine engine to flow over a turbine blade at a lower static pressure than the diverted air. Advantageously, as the diverted air is relatively cool, use of a conventional TOBI nozzle may be eliminated. Similarly, showerheads on the blade may be eliminated.
Conveniently, the diverted air may also be used to seal a rear bearing compartment of the engine.
In accordance with an aspect of the present invention, there is provided a turbine engine including a compressor section to compress intake air into high pressure air and intermediate pressure air; a combustion section in flow communication with the compressor section, to combust fuel with compressed air; a turbine section in flow communication with combustion gases from the combustion section, the turbine section comprising a rotating turbine blade wherein static pressure at the turbine blade is lower than the pressure of the intermediate pressure air; and a conduit having an inlet in flow communication with the intermediate pressure air and an outlet in flow communication with the turbine blade, thereby guiding the intermediate pressure air over the turbine blade.
Other aspects and features of the present invention will become apparent to those of ordinary skill in the art upon review of the following description of specific embodiments of the invention in conjunction with the accompanying figures.
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Astle Jeffrey W.
Look Edward K.
Pratt & Whitney Canada Corp.
Rodriguez Hermes
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