US 4,240,250 A · Noise reducing air inlet for gas turbine engines

Abstract

A noise-suppressing air inlet having two coaxially arranged airflow channels to supply inlet air to a gas turbine engine is disclosed. The outer airflow channel has an annular cross-sectional geometry and is formed between the inner wall of a tubular outer cowling which forms the forward portion of the engine housing and the outer wall of a tubular inner cowling that is coaxially mounted within the outer cowling. The inner airflow channel is formed between the inner wall of the inner cowling and a forward projecting central hub of the gas turbine engine. Major portions of the walls of both the inner and outer cowling include sound attenuating panels to suppress noise propagating in the forward direction through both airflow channels of the air inlet. The inner cowling is supported within the outer cowling such that the leading edge of the inner cowling projects forwardly of the outer cowling leading edge. This support is provided by a number of radially extending, circumferentially spaced-apart struts located between the inner wall of the outer cowling and the outer wall of the inner cowling. The struts are aerodynamically contoured and have a hollow interior for the passage of tubing of an aircraft thermal anti-icing system. The two airflow channels are of a height dimension which provides near optimal noise suppression, thus resulting in minimal air inlet length and minimum length to diameter ratio for a given sound suppression level. Minimizing the length to diameter ratio reduces the airload on the inlet structure during various aircraft maneuvers, reduces the overall weight of the air inlet and, since the outer surface area of the air inlet is thereby minimized, results in less drag.

Claims6

Dependent claims

A noise suppressing air inlet for use in combination with a gas turbine engine that is encased in a housing and includes a compressor stage, said air inlet comprising:

a generally tubular outer cowling for forming a forward end of said engine housing and having an annular leading edge, said outer cowling having an inner wall and an outer wall with said inner wall defining an airflow duct for directing airflow to said compressor stage, at least a portion of said inner wall a sound absorbing surface;
a generally tubular inner cowling having an annular leading edge, an inner wall and an outer wall, said inner cowling coaxially mounted at a fixed position within said outer cowling, said inner cowling having an annular leading edge positioned forwardly of said annular leading edge of said outer cowling, at least a portion of said inner and outer walls of said inner cowling having a sound absorbing surface, said inner cowling partitioning said airflow duct into an inner airflow channel defined by said inner wall of said inner cowling and an annular outer airflow channel defined between said outer wall of said inner cowling and said inner wall of said outer cowling, said inner and outer airflow channels extending substantially over the entire axial length of said air inlet;
and,
a plurality of struts for mounting said inner cowling within said outer cowling, said struts being circumferentially spaced apart from one another and extending radially from said outer wall of said inner cowling to said inner wall of said outer cowling.

1 more element

In an aircraft gas turbine engine having an airflow channel within a generally tubular engine cowling for supplying ambient air to said gas turbine engine, said engine cowling being mounted to extend forwardly from said gas turbine engine, said airflow channel being defined by an inner wall of said engine cowling which extends in spaced apart relationship with an outer wall of said engine cowling, said inner and outer walls of said engine cowling being interconnected to define an annular leading edge wherein predetermined regions of said engine cowling inner wall include sound absorbent regions, the improvement comprising:

a generally tubular inner cowling having an annular leading edge and spaced apart inner and outer walls which extend rearwardly from said annular leading edge of said inner cowling and converge with one another to form a relatively sharp trailing edge, said inner cowling being mounted coaxially within said airflow channel of said engine cowling to divide substantially the entire length of said airflow channel into an annular outer airflow channel defined between said outer wall of said inner cowling and said inner wall of said engine cowling and an inner airflow channel defined by said inner wall of said inner cowling, said inner cowling having a length dimension sufficient to position said annular leading edge of said inner cowling forwardly of said annular leading edge of said engine cowling, said inner and outer walls of said inner cowling each including sound absorbent regions, said inner cowling being dimensioned to establish the height of said inner and outer airflow channels for propagation of a major portion of forwardly propagating engine noise through said outer airflow channel;
and
a plurality of struts circumferentially spaced apart from one another and extending radially between said inner cowling and said engine cowling for securely mounting said inner cowling in said airflow channel of said engine cowling.

Dependencies are inferred from the claim text.

Noise reducing air inlet for gas turbine engines

Life of this patent

Noise reducing air inlet for gas turbine engines

Life of this patent

Abstract

Claims6