Blade neck transition

Patent metadata

Field	Value
Publication number	US-11149550-B2
Application number	US-201916270080-A
Country	US
Kind code	B2
Filing date	Feb 7, 2019
Priority date	Feb 7, 2019
Publication date	Oct 19, 2021
Grant date	Oct 19, 2021

Abstract

A blade for use with a gas turbine engine includes an attachment and an airfoil. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of intersecting ribs transitioning from an airfoil cross sectional geometry to an attachment cross section geometry.

First claim

What is claimed is:

1. A blade, comprising:
a set of intersecting ribs extending from a first radial plane of an airfoil to second radial plane of an attachment proximate a root, the set of intersecting ribs comprising a radial airfoil cross sectional geometry at the first radial plane and a radial attachment cross sectional geometry at the second radial plane, the radial airfoil cross sectional geometry being different from the radial attachment cross sectional geometry, wherein the set of intersecting ribs comprises a first rib and a second rib forming an angle, wherein the angle increases as the set of intersecting ribs transitions from the second radial plane of the attachment to the first radial plane of the airfoil.

2. The blade of claim 1 , wherein the set of intersecting ribs further comprises:
a set of airfoil ribs comprising:
a first airfoil rib extending in a first direction within the radial airfoil cross sectional geometry;
a second airfoil rib extending in a second direction within the radial airfoil cross sectional geometry, the second direction being different from the first direction; and

a set of attachment ribs comprising:
a first attachment rib extending in a circumferential direction within the radial attachment cross sectional geometry;
a second attachment rib disposed aft of the first attachment rib and extending in the circumferential direction within the radial attachment cross sectional geometry;
a third attachment rib disposed between the first attachment rib and the second attachment rib and extending in an axial direction within the radial attachment cross sectional geometry, wherein
the set of airfoil ribs extends radially inward from the radial airfoil cross sectional geometry and transitions into the set of attachment ribs at the radial attachment cross sectional geometry.

3. The blade of claim 2 , wherein the first airfoil rib transitions into a first portion of the first attachment rib, a first portion of the second attachment rib, and a first portion of the third attachment rib, and wherein the second airfoil rib transitions into a second portion of the first attachment rib, a second portion of the second attachment rib, and a second portion of the third attachment rib.

4. The blade of claim 3 , wherein the first attachment rib consists of the first portion of the first attachment rib and the second portion of the first attachment rib, wherein the second attachment rib consists of the first portion of the second attachment rib and the second portion of the second attachment rib, and wherein the third attachment rib consists of the first portion of the third attachment rib and the second portion of the third attachment rib.

5. The blade of claim 2 , further comprising an airfoil pressure wall, an airfoil suction wall, a first attachment wall, and second attachment wall disposed circumferentially opposite the first attachment wall,
wherein the first airfoil rib and the second airfoil rib define a first triangular cavity with the airfoil pressure wall within the radial airfoil cross sectional geometry,
wherein the first airfoil rib and the second airfoil rib define a second triangular cavity with the airfoil suction wall within the radial airfoil cross sectional geometry,
wherein the first attachment rib, the second attachment rib, the third attachment rib, and the first attachment wall define a first quadrilateral shaped cavity,
wherein the first attachment rib, the second attachment rib, the third attachment rib, and the second attachment wall define a second quadrilateral shaped cavity,
and wherein the first triangular cavity transitions into the first quadrilateral shaped cavity and the second triangular cavity transitions into the second quadrilateral shaped cavity as the set of airfoil ribs transitions to the set of attachment ribs.

6. The blade in claim 1 , wherein the first rib and the second rib define a second angle that decreases as the set of intersecting ribs transitions from the first plane of the airfoil to the second radial plane of the attachment.

7. The blade of claim 1 , wherein the set of intersecting ribs partially defines a cavity that is further defined by a first set of control points around a first perimeter of the cavity in the radial airfoil cross sectional geometry and a second set of control points around a second perimeter of the cavity in the radial attachment cross sectional geometry, wherein a first control point subset of the first set of control points transition from a first non-linear shape at the first radial plane in the radial airfoil cross sectional geometry to a first linear shape defined by a second control point subset of the second set of control points in the radial attachment cross sectional geometry at the second radial plane.

8. The blade of claim 7 , wherein the first subset of control points form a first corner of the cavity in the airfoil and the second subset of control points form a side of the cavity in the attachment.

9. The blade of claim 8 , wherein a third control point subset of the first set of control points transition from a second linear shape in the radial airfoil cross sectional geometry to a second non-linear shape defined by a fourth control point subset of the second set of control points at the radial attachment cross sectional geometry, wherein the third subset of control points form a side of the cavity in the airfoil and the fourth subset of control points form a second corner of the cavity in the attachment.

10. The blade of claim 7 , wherein the first perimeter of the cavity is 3-sided and the second perimeter of the cavity is 4-sided.

11. A blade, comprising:
an airfoil having a leading edge and a trailing edge;
an attachment;
a first set of intersecting internal ribs defining a first angle that increases as the first set of intersecting internal ribs extend radially inward from the airfoil to the attachment, the first set of intersecting internal ribs comprising:
a set of airfoil ribs having a radial airfoil cross sectional geometry, the set of airfoil ribs comprising:
a first airfoil rib extending in a first direction within the radial airfoil cross sectional geometry;
a second airfoil rib extending in a second direction within the radial airfoil cross sectional geometry, the second direction being different from the first direction; and

a set of attachment ribs having a radial attachment cross sectional geometry, the set of attachment ribs comprising:
a first attachment rib extending in a circumferential direction within the radial attachment cross sectional geometry;
a second attachment rib disposed aft of the first attachment rib and extending in the circumferential direction within the radial attachment cross sectional geometry;
a third attachment rib disposed between the first attachment rib and the second attachment rib and extending in an axial direction within the radial attachment cross sectional geometry, wherein the set of airfoil ribs extends radially inward from the radial airfoil cross sectional geometry and transitions into the set of attachment ribs at the radial attachment cross sectional geometry;

a second set of intersecting internal ribs disposed aft of the first set of intersecting internal ribs;
a third set of intersecting internal ribs disposed aft of the second set of intersecting internal ribs; and
a fourth set of intersecting internal ribs disposed aft of the third set of intersecting internal ribs.

12. The blade of claim 11 , wherein the first set of intersecting internal ribs further comprises a first rib aft surface and the second set of intersecting internal ribs further comprises a second rib forward surface,

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Spangler Brandon W
• Pack David R

Classifications

• Y02T50/60

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

• F01D5/187

  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

• B22C9/10

  Cores; Manufacture or installation of cores {(breaker cores B22C9/084)} · CPC title

• F05D2230/211

  by precision casting, e.g. microfusing or investment casting · CPC title