Integral compressor housing of gas turbine engines

Details Integral compressor housing of gas turbine engines Integral compressor housing of gas turbine engines

2005-11-29

2005-11-29

Kim, Ted (Department: 3746)

Power plants

Combustion products used as motive fluid

Process

C060S782000, C060S785000, C060S787000

Reexamination Certificate

active

06968697

ABSTRACT:
A turbine engine compressor design utilizing multiple component integration, thereby reducing the number of required engine components. In conventional compressor designs, a multiple component system makes it difficult to predict the structural behaviors due to thermal and mechanical loading during transient conditions. The compressor design of the present invention has three main parts: a forward bearing housing, a bell-mouth (heat shield) and a coupled impeller shroud/diffuser. Such a design achieves the design objectives of the present invention, including reducing weight, reducing cost, minimizing tolerance build up and improving aerodynamic performance by utilizing multiple component integration for multiple modes of engine operation.

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