Gas turbine engine airfoil fairing with rib having radial notch
AssigneeRaytheon Technologies Corporation
InventorsTyler G. Vincent, Chang Gao, Bryan P. Dube
Life of this patent
Estimating the term…
Abstract
An airfoil fairing includes an airfoil section that is formed of a fiber-reinforced composite wall. The airfoil section has first and second radial ends, pressure and suction sides, leading and trailing ends that join the pressure and suction sides, an internal cavity, and a rib that extends radially in the internal cavity. The rib has a radial rib end at the first radial end of the airfoil section and extends across the internal cavity from a first rib side at the pressure side to a second rib side at the suction side. The rib defines at the radial end first and second shoulders. The first and second shoulders define a radial notch there between.
Claims21
An airfoil fairing comprising:
- an airfoil section formed of a fiber-reinforced composite wall, the airfoil section having first and second radial ends, pressure and suction sides, leading and trailing ends joining the pressure and suction sides, an internal cavity, and a rib extending radially in the internal cavity, the rib having a radial rib end at the first radial end of the airfoil section and extending across the internal cavity from a first rib side at the pressure side to a second rib side at the suction side, the rib defining at the radial end first and second shoulders, the first and second shoulders defining a radial notch there between, each of the first and second shoulders having an apex defined at a farthest perpendicular distance from a reference line that intersects the respective first or second shoulder at the pressure side or the suction side and that is tangent to the radial notch, the radial notch defined between the apex of the first shoulder and the apex of the second shoulder.
A gas turbine engine comprising:
- a compressor section;
- a combustor in fluid communication with the compressor section;
- and
- a turbine section in fluid communication with the combustor, the turbine section having vanes disposed about a central axis of the gas turbine engine, each of the vanes includes:
- an airfoil fairing including an airfoil section formed of a fiber-reinforced composite wall, the airfoil section having first and second radial ends, pressure and suction sides, leading and trailing ends joining the pressure and suction sides, an internal cavity, and a rib extending radially in the internal cavity, the rib having a radial rib end at the first radial end of the airfoil section and extending across the internal cavity from a first rib side at the pressure side to a second rib side at the suction side, the rib defining at the radial end first and second shoulders, the first and second shoulders defining a radial notch there between, the rib at the radial rib end defining a lateral rib span from the pressure and to the suction side of the airfoil section, the radial notch defining a lateral notch span between shoulder apexes of the first and second shoulders, and the lateral notch span is 40% to 70% of the lateral rib span.
Dependencies are inferred from the claim text.