Steam heated flange for thermal gradient control
AssigneeRtx Corporation
InventorJon Erik Sobanski
Life of this patent
Estimating the term…
Abstract
A turbine engine assembly includes a first case structure with a first flange and a second case structure that includes a second flange. The second flange is configured for securement to the first flange at a connection interface. At least one steam conduit is in thermal communication with the connection interface and configured to receive a portion of a flow of steam to heat the connection interface. Heating the connection interface provides for control of a thermal gradient generated by a difference in temperature in temperatures on either side of the connection interface.
Claims21
A turbine engine assembly comprising:
- a compressor section where an inlet airflow is compressed;
- a combustor section where the compressed inlet airflow is mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path defined along an engine longitudinal axis;
- a turbine section through which the exhaust gas flow expands to generate a mechanical power output;
- an evaporator system generating a flow of steam;
- a first case structure including a first flange, wherein the first flange is a full round structure that is disposed transverse to and about the engine longitudinal axis;
- a second case structure including a second flange, wherein the second flange is a full round structure that is disposed transvers to and about the engine longitudinal axis, the second flange configured for securement to the first flange at a connection interface;
- and
- at least one steam conduit in thermal communication with the connection interface and configured to receive a portion of the flow of steam to heat the connection interface, wherein each of the first flange and the second flange includes an outer peripheral surface transverse to the engine longitudinal axis and the at least one steam conduit is supported on the outer peripheral surface.
(canceled)
An aircraft propulsion system comprising:
- a core engine section defining a core flow path where an inlet airflow is compressed, mixed with fuel and ignited to generate an exhaust gas flow that is communicated through a core flow path defined along an engine longitudinal axis;
- a condenser where water is extracted from the exhaust gas flow;
- an evaporator system where thermal energy from the exhaust gas flow is utilized to generate a steam flow for injection into the core flow path;
- a first case structure including a first flange, wherein the first flange is a full round structure that is disposed transverse to and about the engine longitudinal axis;
- a second case structure including a second flange, wherein the second flange is a full round structure that is disposed transvers to and about the engine longitudinal axis, the second flange configured for securement to the first flange at a connection interface;
- and
- at least one steam conduit in thermal communication with an outer peripheral surface of the connection interface and configured to receive a steam flow from the evaporator system to heat the connection interface;
- a control valve configured to control the flow of steam into the at least one steam conduit;
- and
- a controller programmed to operate the control valve to maintain a temperature differential of the connection interface within a defined range by adjusting a flow of steam through the at least one steam conduit.
18-20. (canceled)
Dependencies are inferred from the claim text.