Thermal barrier structure

• US 5,236,151 A
• Filed: 12/23/1991
• Issued: 08/17/1993
• Est. Priority Date: 12/23/1991
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Oliver, Reed R., Hagle, Michael P.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): BIDWELL, ANNE
• Application Number:
  US07/812,665
• Time in Patent Office: 603 Days
• Field of Search: 244/117 R, 244/117 A, 244/158 A, 244/123, 165/135
• US Class Current: 244/117.00A
• CPC Class Codes: B64C 1/38 Constructions adapted to reduce effects of aerodynamic or other external heating
• CPC Class Codes: B64G 1/226 Special coatings for spacecraft
• CPC Class Codes: B64G 1/58 Thermal protection, e.g. heat shields

Abstract

An insulative panel is attachable to a structure to thermally protect the structure. The insulative panel includes a piece of a compliant, porous material. A support base is bonded to a first side of the piece of porous material, the support base including means for attaching the support base to the structure that is to be protected. A skin made of a thermally resistant material is bonded to a second side of the piece of porous material. Preferably, the porous material is a piece of porous ceramic foam having an apparent density of less than about 25 percent, the support base is a piece of nonporous ceramic material, and the skin is a ceramic thermal barrier coating that is plasma sprayed onto the porous material.

Claims

1. An insulative panel that is attachable to a structure to protect the structure, comprising:

a piece of a compliant, porous material;

a support base bonded to a first side of the piece of porous material, the support base including means for attaching the support base to a structure;

a skin made of a thermally resistant material bonded to a second side of the piece of porous material; and

means for directing a flow of air through the piece of porous material.

2. An attachable thermal barrier structure, comprising:

a piece of compliant, porous ceramic foam;

a support base made of a nonporous ceramic material bonded to a first side of the piece of ceramic foam, the support base including means for attaching the support base to an underlying structure;

a skin made of a nonporous ceramic material bonded to a second side of the piece of porous ceramic foam; and

means for directing a flow of air through the piece of porous ceramic foam.

3. An aircraft structure protected against external heating and having a reduced radiation signature, comprising:

an externally exposed piece of the structure; and

an insulative panel that is attachable to the structure to protect said structure, said panel comprised of

a piece of compliant, porous material,

a support base bonded to a first side of the piece of porous material, the support base including means for attaching the support base to the structure,

a skin made of a thermally resistant material bonded to a second side of the piece of porous material, and

means for directing a flow of air through the piece of porous material in a direction generally parallel to the skin.

4. The aircraft structure of claim 3, wherein the externally exposed piece of the structure is an exhaust nozzle of a gas turbine engine.