Turbomachine Combustion Chamber Cooling Segments
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Solution Overview
Problem
Constant volume turbomachine combustion chambers experience temperature peaks and mechanical strength issues due to radiative effects and shock waves, with the radially outer portion of the combustion chamber body not being effectively cooled.
Innovation Solution
Incorporation of cooling segments distributed around the combustion tubes, along with perforated rotary discs that selectively open and close the combustion tubes and cooling segments, allowing compressed air to cool the outer periphery of the combustion chamber body.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If constant volume combustion is used to achieve high thermal efficiency, then combustion temperature peaks occur which worsen the mechanical strength of combustion tubes and body
Solution Approach 1:
The combustion chamber body is segmented into multiple zones with different cooling requirements. The body is divided into a radially inner portion and a radially outer portion, each served by dedicated cooling passages. This segmentation allows targeted cooling of the combustion tubes while managing the thermal load from constant volume combustion.
Solution Approach 2:
Different regions of the combustion chamber body are provided with different cooling arrangements. The radially inner portion receives cooling from compressed air in central conduits, while the radially outer portion is cooled by separate cooling passages. This local differentiation addresses the varying thermal conditions at different radial positions.
2Use of energy by moving object
If constant volume combustion is used to achieve high thermal efficiency, then radiative heating worsens the overall temperature of the body
Solution Approach 1:
The cooling system is segmented into multiple independent cooling circuits. One circuit cools the radially inner portion through central conduits, while another circuit cools the radially outer portion through dedicated cooling passages. This segmentation enables independent temperature control of different body regions exposed to radiative heating.
Solution Approach 2:
The cooling arrangement provides locally optimized thermal management. The radially outer portion, which experiences significant radiative heating from combustion, is equipped with dedicated cooling passages that deliver cooled air directly to this region, creating a local quality difference in thermal protection.
3Temperature
If cooling passages are added to cool the radially outer portion, then the device complexity increases
Solution Approach 1:
The compressed air supply system serves multiple functions simultaneously. The same compressed air source provides cooling to both the radially inner portion (through central conduits) and the radially outer portion (through cooling passages), eliminating the need for separate cooling sources and reducing overall system complexity.
Solution Approach 2:
The cooling passages for the radially outer portion are integrated into the existing combustion chamber structure. The cooling passages are formed within the body itself, merging the cooling function with the structural components rather than adding separate external cooling systems.
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 cools the outer portion of the combustion chamber body, mitigating temperature peaks and mechanical stress, thereby enhancing the overall thermal situation and mechanical strength.
Implementation Method 1
the body includes a plurality of cooling segments which extend mainly in the direction of the main axis, which are distributed in a ring about said main axis and around the combustion tubes
Implementation Method 2
The radially inner portion of the body is cooled by the compressed air circulating in the central conduit
Implementation Method 3
the temperature peaks generated by the constant volume combustion modes lead to an increase in the overall temperature of the body by radiative effect
Data Source
AI summary
A combustion chamber of an aircraft turbomachine having a main axis includes: a body of revolution coaxial with the main axis having a plurality of combustion tubes extending mainly in the direction of the main axis and being distributed in a ring about the main axis; a first perforated rotary disc mounted at a first axial end of the body and rotatable about the main axis to selectively open or close a first end of each of the combustion tubes; and a second perforated rotary disc mounted at a second axial end of the body and rotatable about the main axis to selectively open or close a second end of each of the combustion tubes. The body includes a plurality of cooling segments extending mainly in the direction of the main axis, which are distributed in a ring about the main axis and around the combustion tubes.