Process for cooling the blades of thermal turbomachines
AssigneeMarresearch Gesellschaft fuer Forschung und Entwicklung GmbH
InventorWalter Sibbertsen
Life of this patent
Estimating the term…
Abstract
Cooling air flows over the inner wall of the blade, and emerges through sl orifices provided in the blade jacket in the region of the boundary layer. The cooling air is admitted tangentially into an eddy tube provided with a closure and with a throttle in the region of the latter. The cooling air flow, which is cooled after flowing through the closure is fed into the blades and, after passing over the inner wall of the blade jacket, escapes from each blade in the region of the boundary layer. The heated air flow which escapes from the throttle is evacuated from the blade region. This airflow can be mixed with the cooling air or be introduced into the main gas flow.
Claims30
A method for cooling heat-stressed structural elements of turbomachines, in which cooling air flows past wall-surfaces of the structural elements to be cooled, subjected to heat, of said structural elements, wherein the cooling air flows tangentially into a vortex-tube consisting of a cylindrical vortex-chamber, having two choke-elements at the end-sections, at a location between the said choke-elements that is in the vicinity a one of said choke-elements that is provided with an orifice-plate-like inflow-section, and wherein the flow after entering the vortex-tube is divided into two partial flows of cooling air, one of which, after flowing through the choke-element with an orifice-plate-like inflow-section, is cooled in relation to the temperature of the cooling air flowing into said vortex-tube and is fed to the wall surfaces to be cooled, while the other partial flow of cooling air is led away from the vicinity of the structural elements.
A blade for a turbomachine which, when the said engine is in operation, is heat-stressed and which is adapted to be cooled with cooling air through cooling channels formed in said blade, the said cooling air emerging through small openings in the wall of the blade, wherein a vortex-tube is arranged in the blade, inflow-nozzles of the vortex-tube being arranged tangentially in the vicinity of an orifice-plate-like choke-element and being connected to a cooling-air channel in a manner for dividing cooling air from said cooling-air channel into a partial flow of cooling air that is directed through said choke-element so as to be cooled still further and passed into cooling channels in said blade, and into a remaining partial flow of cooling air that is directed in a manner so as to emerge through a hot-air outlet of a nozzle-like choke-element as hot air.
A blade for a turbomachine which, when said engine is in operation, is heat-stressed and which is adapted to be cooled with cooling air through cooling channels formed in said blade, the said cooling air emerging through small openings in the wall of the blade, wherein a vortex-tube with a vortex-chamber housing having tangentially aligned inflow-nozzles that are connected to a cooling-air channel is arranged in the blade, and wherein a vortex-space of the vortex-chamber housing comprises two flow-outlet apertures that are arranged coaxially with respect to a centreline of the vortex-chamber housing, one of the said apertures being connected to a diffusor and the other to an orifice-plate-like choke-element.
An apparatus for cooling a heat-stressed structural element of a turbomachine, in which cooling air flows past wall surfaces thereof, and is subjected to heat, wherein:
- a source of cooling air is connected to a vortex-tube in which tangentially directed inflow-nozzles for cooling air are provided for directing cooling air into a chamber of the vortex-tube between an orifice-plate-like choke-element and a nozzle-choke element,
- a cold air outlet located downstream of said orifice-plate-like choke-element is connected to cooling channels in the heat-stressed structural element,
- and a hot-air outlet of the nozzle-like choke-elements is connected to a gas flow channel downstream of a combustion-chamber.
Dependencies are inferred from the claim text.