Airfoil for a turbomachine

Patent metadata

Field	Value
Publication number	US-11248474-B2
Application number	US-201916434385-A
Country	US
Kind code	B2
Filing date	Jun 7, 2019
Priority date	Jun 14, 2018
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

An airfoil for disposition and exposure to flow in a hot gas duct of a turbomachine is provided. The airfoil has a suction-side wall and a pressure-side wall with respect to its exposure to the flow in the gas duct, the side walls converging in an upstream end region toward a leading edge and converging in a downstream end region toward a trailing edge. The airfoil further has a cavity structure therein which is enclosed between an inner wall surface of the suction-side wall and an inner wall surface of the pressure-side wall when viewed in a cross-sectional plane axially parallel to a longitudinal axis of the turbomachine. When viewed in the cross-sectional plane, at least one of the inner wall surfaces, normalized to a mean camber line of the airfoil as a reference, extends with a change in curvature into at least one of the end regions in such a way that a clearance width of the cavity structure is increased at the at least one end region.

First claim

What is claimed is:

1. An airfoil for disposition and exposure to flow in a hot gas duct of a turbomachine, the airfoil comprising:
a suction-side wall;
a pressure-side wall with respect to exposure to the flow in the gas duct, the suction-side wall and pressure-side walls converging in an upstream end region toward a leading edge and converging in a downstream end region toward a trailing edge; and
a cavity structure enclosed between a first inner wall surface of the suction-side wall and a second inner wall surface of the pressure-side wall when viewed in a cross-sectional plane axially parallel to a longitudinal axis of the turbomachine and having a central section about a mean camber line of the airfoil, the central section including a midpoint of the airfoil located between the leading edge and the trailing edge along the mean camber line, the first and second inner wall surfaces converging in the central section about the mean camber line without a change in curvature in the central section toward the upstream and downstream end regions,
wherein, when viewed in the cross-sectional plane, at least one of the first and second inner wall surfaces, normalized to the mean camber line of the airfoil as a reference, extends with a change in curvature into both of the upstream and downstream end regions in such a way that a clearance width of the cavity structure in the upstream and downstream end regions is increased at both upstream and downstream end regions with respect to extensions of the first and second inner wall surfaces meeting at the upstream and downstream end regions and wherein the suction-side or pressure-side wall forming the at least one first or second inner wall surface having the change in curvature has a wall thickness in the central section which is reduced by at least 5% and no more than 35% in the region of the change in curvature when viewed in the cross-sectional plane; wherein the at least one of the first and second inner wall surfaces has exactly two changes in curvature.

2. The airfoil as recited in claim 1 wherein the at least one first and second inner wall surfaces has a smooth shape at least in the region of the change in curvature when viewed in the cross-sectional plane.

3. The airfoil as recited in claim 1 , wherein, as considered with respect to a duct height of the gas duct, the at least one first or second inner wall surface extends with the change in curvature over an entire duct height.

4. The airfoil as recited in claim 1 , wherein, as considered with respect to a duct height of the gas duct, defined between 0% radially inwardly and 100% radially outwardly, the at least one first or second inner wall surface extends with the change in curvature at least over a region between 0% and 20%.

5. The airfoil as recited in claim 1 , wherein, as considered with respect to a duct height of the gas duct, defined between 0% radially inwardly and 100% radially outwardly, the at least one first inner wall surface extends with the change in curvature at least over a region between 80% and 100%.

6. The airfoil as recited in claim 1 , wherein both the first and second inner wall surfaces extend with a respective change in curvature into at least one of the upstream and downstream end regions.

7. The airfoil as recited in claim 1 , wherein the cavity structure forms a continuous cavity between the upstream and downstream end regions when viewed in the cross-sectional plane.

8. The airfoil as recited in claim 1 , wherein the cavity structure forms a continuous cavity between the first and second inner wall surfaces when viewed in the cross-sectional plane.

9. The airfoil as recited in claim 1 , wherein the suction-side and pressure-side walls are each in themselves uninterruptedly continuous so that side wall material between the first and second inner wall surfaces and a respective outer wall surface is free of discontinuities.

10. A turbine module having an airfoil as recited in claim 1 .

11. A method of operating an airfoil as recited in claim 1 in a turbomachine, the method comprising flowing a cooling fluid through the cavity structure during operation of the turbomachine.

12. The method as recited in claim 11 wherein the turbomachine is a jet engine.

13. The airfoil as recited in claim 1 , wherein each of the at least one of the first and second inner wall surfaces has exactly two changes in curvature.

14. An airfoil for disposition and exposure to flow in a hot gas duct of a turbomachine, the airfoil comprising:
a suction-side wall;
a pressure-side wall with respect to exposure to the flow in the gas duct, the suction-side wall and pressure-side walls converging in an upstream end region toward a leading edge and converging in a downstream end region toward a trailing edge; and
a cavity structure enclosed between a first inner wall surface of the suction-side wall and a second inner wall surface of the pressure-side wall when viewed in a cross-sectional plane axially parallel to a longitudinal axis of the turbomachine and having a central section about a mean camber line of the airfoil, the central section including a midpoint of the airfoil located between the leading edge and the trailing edge along the mean camber line, the first and second inner wall surfaces converging in the central section about the mean camber line without a change in curvature in the central section toward the upstream and downstream end regions,
wherein, when viewed in the cross-sectional plane, at least one of the first and second inner wall surfaces, normalized to the mean camber line of the airfoil as a reference, extends with a change in curvature into both of the upstream and downstream end regions in such a way that a clearance width of the cavity structure in the upstream and downstream end regions is increased at both upstream and downstream end regions with respect to extensions of the first and second inner wall surfaces meeting at the upstream and downstream end regions,
wherein the at least one of the first and second inner wall surfaces has exactly two changes in curvature.

15. The airfoil as recited in claim 14 , wherein each of the at least one of the first and second inner wall surfaces has exactly two changes in curvature.

Assignees

• MTU Aero Engines AG

Inventors

• Ertl Franz-Joseph
• Hackenberg Hans-Peter
• Buck Alexander
• Ostermeir Oskar

Classifications

• F05D2250/713

  inflexed · CPC title

• F05D2250/71

  curved · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title