Partially-metallic blade for a gas turbine

• US 5,634,771 A
• Filed: 09/25/1995
• Issued: 06/03/1997
• Est. Priority Date: 09/25/1995
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Howard, Walter D., Ingling, Theodore R., Bachrach, William E.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Sgantzos, Mark
• Application Number:
  US08/533,478
• Time in Patent Office: 617 Days
• Field of Search: 416/241 A, 416/229 R, 416/229 A, 416/230, 416/232
• US Class Current: 416/241.00A
• CPC Class Codes: F01D 5/147 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 Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A lightweight, impact-resistant gas turbine blade, such as an aircraft engine fan blade, has a metal solid section, composite or structural/syntactic foam segments, and metal solid spars all attached together to define an airfoil portion. The solid section includes the leading edge, blade tip, and trailing edge. The segments together are bounded in part by the solid section near the leading edge, blade tip, and trailing edge. The solid spars separate and are attached to the segments.

Claims

1. A gas turbine aircraft engine fan blade comprising:

a shank portion;

a solid section;

a multiplicity of spaced-apart segments; and

a plurality of solid spars, wherein said solid section, said segments, and said solid spars are attached together to define a rotatable airfoil portion, and wherein said rotatable airfoil portion includes;

a) a leading edge;

b) a trailing edge;

c) a pressure side;

d) a suction side, said sides joined together at said edges to define an airfoil shape having a chord line extending from said leading edge to said trailing edge and having a thickness-wise direction perpendicular to said chord line and extending from said pressure side to said suction side;

e) a blade root attached to said shank portion;

f) a blade tip; and

g) a radial axis extending outward toward said blade tip and inward toward said blade root,

wherein said solid section consists essentially of a metal material, said solid section including partially said pressure and suction sides proximate and including said blade tip from said leading edge to said trailing edge and proximate and including said leading and trailing edges from said blade root to said blade tip,

wherein said segments consist essentially of a material selected from the group consisting of composites, structural foams, syntactic foams, and mixtures thereof, said segments together bounded in part by said solid section proximate said blade tip, said leading edge, and said trailing edge, and

wherein said solid spars separate and are attached to said segments, said solid spars consisting essentially of a metal material.

2. The gas turbine blade of claim 1, wherein said segments extend generally thickness-wise from said pressure side to said suction side.

3. The gas turbine blade of claim 2, wherein said solid spars include a first spar extending generally radially from said blade root to proximate said blade tip and extending generally thickness-wise from said pressure side to said suction side, and wherein said solid spars include a second spar extending generally chordwise from proximate said leading edge to proximate said trailing edge and extending generally thickness-wise from said pressure side to said suction side.

4. The gas turbine blade of claim 3, wherein said first spar has an end attached to said solid section proximate said blade tip, and wherein said second spar has two ends each attached to said solid section proximate a corresponding one of said leading and trailing edges.

5. The gas turbine blade of claim 3, wherein said first and second spars intersect and wherein said solid spars include a third spar extending from said intersection at an angle of generally forty-five degrees from said radial axis and extending generally thickness-wise from said pressure side to said suction side.

6. The gas turbine blade of claim 1, wherein said solid section further includes entirely said suction side such that said segments are abutted by said solid section towards said suction side.

7. The gas turbine blade of claim 6, wherein said solid spars include a first spar extending generally radially from said blade root to proximate said blade tip and extending generally thickness-wise from said pressure side to proximate said suction side, and wherein said solid spars include a second spar extending generally chordwise from proximate said leading edge to proximate said trailing edge and extending generally thickness-wise from said pressure side to proximate said suction side.

8. The gas turbine blade of claim 7, wherein said first spar has an end attached to said solid section proximate said blade tip, and wherein said second spar has two ends each attached to said solid section proximate a corresponding one said leading and trailing edges.

9. The gas turbine blade of claim 8, wherein said first and second spars intersect and wherein said solid spars include a third spar extending from said intersection at an angle of generally forty-five degrees from said radial axis and extending generally thickness-wise from said pressure side to proximate said suction side.

10. The gas turbine blade of claim 1, wherein said solid spars includes a core spar extending generally chordwise from proximate said leading edge to proximate said trailing edge, extending generally radially from said blade root to proximate said blade tip, and thickness-wise spaced apart from said pressure and suction sides.