Blower Compressor Bleed Opening for Cabin Air Contaminant Removal
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Solution Overview
Problem
Current aircraft cabin pressurization systems using engine bleed air from gas turbine engines reduce engine efficiency and increase fuel consumption, necessitating an improved air pressurization method that utilizes lower pressure air from the bypass duct and compresses it before delivery to the cabin.
Innovation Solution
An air pressurization system comprising a blower compressor mechanically coupled to a gas turbine engine's spool, with a compressor wheel and housing that includes a bleed opening for contaminants, and a delivery line to convey compressed air to the aircraft's airframe system, along with a bleed air line and seal assembly to manage oil and air flow effectively.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If high pressure air is bled from the gas turbine engine compressor section, then cabin pressurization is achieved, but engine efficiency reduces and fuel consumption increases
Solution Approach 1:
The patent extracts air from the bypass duct (a lower pressure source) rather than from the compressor section, and uses a separate blower compressor to provide the necessary compression for cabin pressurization. This separation allows the engine to operate more efficiently while still achieving cabin pressurization.
Solution Approach 2:
The blower compressor acts as an intermediary device that takes low-pressure air from the bypass duct and compresses it to the required pressure level for cabin delivery, eliminating the need to bleed high-pressure air directly from the engine compressor section.
2Loss of energy
If air is compressed using a blower compressor driven by the gas turbine engine spool, then cabin pressurization is achieved with reduced fuel consumption, but contaminants in the inlet air must be managed
Solution Approach 1:
The patent extracts contaminants from the inlet air stream using a centrifugal separator that removes particles driven outward by centrifugal force during rotor rotation, and uses a bleed opening to remove contaminants that have been driven outward due to rotor rotation.
Solution Approach 2:
The centrifugal separator and bleed opening act as intermediary removal mechanisms between the inlet air and the compressed air delivered to the cabin, preventing contaminants from entering the cabin while maintaining the compression function.
3Object-affected harmful factors
If a bleed opening is provided in the housing wall to remove contaminants, then cabin air contamination is prevented, but system complexity increases
Solution Approach 1:
The patent merges the contamination removal function into the existing blower compressor housing by providing a bleed opening in the housing wall, rather than adding a separate standalone filtration system. The centrifugal separator is integrated into the rotor assembly itself.
Solution Approach 2:
The rotor itself performs the contamination removal function through its rotation, which generates centrifugal force to drive contaminants outward toward the bleed opening, eliminating the need for separate active contamination removal mechanisms.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution enhances cabin pressurization efficiency by reducing fuel consumption and maintaining engine performance by utilizing lower pressure air from the bypass duct, while effectively managing contaminants and oil to prevent cabin air contamination.
Implementation Method 1
a blower compressor configured to be mechanically coupled to a spool of a gas turbine engine and configured to receive an inlet flow of air from a bypass duct of the gas turbine engine
Implementation Method 2
the bleed opening is for contaminants within the inlet flow of air, which have been driven outward due to the rotation of the rotor, to be bled out of the blower compressor
Data Source
AI summary
A compressor of an aircraft air pressurization system comprises: a rotor configured to be mechanically coupled to a spool of a gas turbine engine; and a housing, wherein the rotor is supported for rotation within the housing about a rotor axis, wherein the rotor and housing define a primary air channel extending between an inlet of the blower compressor for receiving the inlet flow of air and an outlet from which the blower compressor is configured to output pressurized air to a delivery line. The housing further comprises a bleed opening in a wall of the housing between the inlet and the outlet, the bleed opening extending circumferentially about the rotor axis, wherein the bleed opening is for contaminants within the inlet flow of air, which have been driven outward due to the rotation of the rotor, to be bled out of the blower compressor.