Gas Turbine Intake Lining with Angled Holes for Flow Control
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Solution Overview
Problem
Existing gas turbine engine intakes face challenges in controlling airflow separation and shock waves due to cross winds and high incidence conditions, which can lead to inefficiencies and potential damage, and require separate anti-icing and acoustic treatments that increase weight and complexity.
Innovation Solution
A gas turbine engine intake with a lining featuring an array of holes angled differently to attenuate acoustic pressure waves and prevent icing and shock wave formation, utilizing a compressed gas source to actively control airflow and suppress separation, integrated with an active flow control arrangement that includes a valve system and sensors to optimize gas delivery based on operational conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate anti-icing and acoustic treatments are used, then functional requirements are met, but weight and complexity increase
Solution Approach 1:
The patent combines anti-icing holes and acoustic holes into a single integrated lining array. The lining includes both anti-icing holes (angled to prevent ice accretion) and acoustic holes (angled to attenuate sound waves) within one structure, eliminating the need for separate anti-icing and acoustic treatments while maintaining both functions.
Solution Approach 2:
The lining array serves multiple functions simultaneously: anti-icing holes prevent ice formation on the intake surface, acoustic holes reduce noise from the engine, and together they provide flow control to suppress shock waves and separation. This multi-functional design reduces overall system complexity.
2Reliability
If different angled holes are used for acoustic attenuation and anti-icing, then functional performance is improved, but manufacturing complexity increases
Solution Approach 1:
The lining array is designed with different hole angles in different regions: anti-icing holes are angled at specific orientations to prevent ice accretion on the intake surface, while acoustic holes are angled differently to optimize sound wave attenuation. This localized optimization of hole angles for different functions allows each region to perform its specific purpose effectively.
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
The solution effectively minimizes airflow separation and shock wave formation, provides anti-icing functionality, and reduces noise, while minimizing weight and complexity by using a single integrated system that optimizes gas usage and improves engine efficiency.
Implementation Method 1
the holes of the first set of holes are angled a relative to a radial line with respect to the rotational axis and the holes of the second set of holes are angled β relative to the radial line; the angles α and β are different; the first set of holes may be arranged to attenuate acoustic pressure waves
Implementation Method 2
the second set of holes may be arranged to prevent icing and/or the formation of shock waves and/or boundary layer separation
Implementation Method 3
the active flow control arrangement is operable to supply compressed gas to the intake surface to prevent separation of a main air flow (9) passing through the intake from the inlet surface
Implementation Method 4
The first set of holes may be arranged to attenuate acoustic pressure waves
Data Source
AI summary
A gas turbine engine having a rotational axis, an intake and a compressed gas source; the intake includes a lining having a facing which defines an inlet surface and an array of holes; the array of holes includes at least a first set of holes and a second set of holes, the holes of the first set of holes are angled a relative to a radial line and the holes of the second set of holes are angled β relative to the radial line; the angles α and β are different. An active flow control arrangement including a compressed gas supply pipe, a valve arrangement, a controller, a compressed gas distribution pipe may be provided. Compressed gas may be provided to prevent the formation of separation of a main gas flow through the intake and prevent or remove ice accretion.