Appeal No. 2002-1840
Application 09/134,993
turbine components” (specification, page 1). Representative
claim 1 reads as follows:
1. A gas turbine engine cooling system for providing
cooling air to engine components, said system comprising:
a core engine having, in downstream serial flow
relationship, a high pressure compressor, a combustor, and high
pressure turbine drivingly connected to said high pressure
compressor and a core flowpath therethrough;
said high pressure compressor being effective for providing
pressurized air;
a first flowing means for flowing a portion of the
pressurized air to a heat exchanger to cool the portion of the
pressurized air and form the cooling air;
a second flowing means for flowing a first portion of the
cooling air to a compressor impeller for boosting pressure of the
first portion of the cooling air and operable for flowing a
second portion of the cooling air to a turbine cooling means for
cooling components of said high pressure turbine; and
said compressor impeller operably connected to a compressor
disk of said high pressure compressor.
THE PRIOR ART
The references relied on by the examiner to support the
final rejection are:
Zaehring et al. (Zaehring) 4,808,073 Feb. 28, 1989
Liebl 4,961,309 Oct. 9, 1990
Narayana et al. (Narayana) 5,226,785 Jul. 13, 1993
Burrus 5,619,855 Apr. 15, 1997
2
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