Compressor blade for a gas turbine engine

• US 6,206,642 B1
• Filed: 12/17/1998
• Issued: 03/27/2001
• Est. Priority Date: 12/17/1998
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Holmes, Richard A., Matheny, Alfred P., Twelves, Wendell V. Jr.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, NINH H
• Application Number:
  US09/213,696
• Time in Patent Office: 831 Days
• Field of Search: 415/173.1, 415/173.3, 415/173.4, 415/173.5, 416/224, 416/230, 416/231.B, 416/229.R, 416/229.A
• US Class Current: 416/230
• 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 5/20 Specially-shaped blade tips to seal space between tips and stator F01D5/225 takes precedence
• CPC Class Codes: F04D 29/164 of an axial flow wheel
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F05D 2300/501 Elasticity

Abstract

A compressor blade that has a blade root, an airfoil having a first end, and a second end opposite the first end, the second end having at least one edge, and the airfoil is made of a first material having a first modulus of elasticity. A blade platform connects the blade root to the first end of the airfoil, and a flexible seal is connected to the airfoil adjacent the second end, and the seal is made of a second material having a modulus of elasticity that is substantially less than the first modulus of elasticity.

Claims

1. A blade for use in a gas turbine engine, said blade comprising:

a blade root;

an airfoil having a reference axis defined therethrough, said airfoil extending along said axis and having a first end, and a second end opposite said first end, said second end having at least one edge, and said airfoil is made of a first material having a first modulus of elasticity;

a blade platform connecting said blade root to said first end of said airfoil; and

a flexible seal connected to said airfoil adjacent said second end, and said seal is made of a second material having a second modulus of elasticity, said seal having a first layer made of fiber and including a first portion and a second portion, said first portion extends from said airfoil in a direction substantially parallel to said axis and is embedded between a second layer and a third layer, said second portion of said first layer is bonded to said airfoil adjacent said second end said second layer terminates adjacent said edge, said edge is radiused, and said second layer tapers toward said first layer immediately adjacent said edge and said second and third layers of are made of a thermal plastic material;

wherein said second modulus of elasticity is substantially less than said first modulus of elasticity.

2. A blade for use in a gas turbine engine, said blade comprising:

a blade root;

an airfoil having a reference axis defined therethrough, said airfoil extending along said axis and having a first end, and a second end opposite said first end, said second end having at least one edge, and said airfoil is made of a first material having a first modulus of elasticity;

a blade platform connecting said blade root to said first end of said airfoil; and

,

a flexible seal connected to said airfoil adjacent said second end, and said seal is made of a second material having a second modulus of elasticity, said second modulus of elasticity is substantially less than said first modulus of elasticity, said seal having a first layer made of fiber and including a first portion and a second portion, said first portion extends from said airfoil in a direction substantially parallel to said axis and is embedded between a second layer and a third layer, and said second and third layers of are made of a thermal plastic material;

wherein said airfoil includes a channel adjacent said second end, said channel includes a tapered portion, said tapered portion tapers toward said second end, said channel terminates at said second end at two of said edges, and each of said edges is radiused.

3. The blade of claim 2 wherein said second portion of said first layer envelopes a key, and said key is located in said tapered portion of said channel.

4. The blade of claim 3 wherein said key is made of said thermal plastic material.

5. The blade of claim 4 wherein said airfoil includes a notch adjacent said second end, and said key extends into said notch.