Flame prevention device
A gas turbine engine includes an engine casing concentrically disposed around the following: a low pressure compressor; a turbine; and a high pressure compressor having at least one bleed tube and at least one joint proximate to the engine casing; and at least one flame prevention device adapted to cover at least a portion of at least one gas turbine engine component.
1. A gas turbine engine, comprising:
an engine casing concentrically disposed around the following:
a low pressure compressor;
a turbine; and
a high pressure compressor; and
at least one flame prevention device surrounding at least a portion of at least one gas turbine engine component, said at least one flame prevention device comprising a hollow sleeve having at least one layer of a flame retardant material coated with one of a ceramic material, a silicate material, and an aramid fiber material, and said at least one layer of said flame retardant material being treated with a resin.
2. The gas turbine engine of claim 1 , wherein said at least one layer of said flame retardant material comprises at least one woven flame retardant material.
3. The gas turbine engine of claim 2 , wherein said sleeve is flexible and form-fitting.
4. The gas turbine engine of claim 2 , wherein said woven flame retardant material has a weave pattern of any one of the following: plain, twill, basket, Leno, Satin, and Herringbone.
5. The gas turbine engine of claim 1 , wherein said sleeve comprises at least two half shells sealed together.
6. The gas turbine engine of claim 5 , wherein said half shells comprise at least two pieces of a flame retardant ceramic foam.
7. The gas turbine engine of claim 5 , wherein said half shells are sealed together using any one of the following: mechanical fasteners, coatings and adhesives.
8. The gas turbine engine of claim 1 , wherein said at least one gas turbine engine component is at least one of a bleed tube disposed external to the engine casing and connecting a compressor section to a combustion section and an elbow joint connecting an end of said bleed tube to said engine casing.
9. The gas turbine engine of claim 1 , wherein said at least one flame prevention device has a thickness of about 5 mils (127 μm) to about 2000 mils (5.08×10 4 μm).
10. The gas turbine engine of claim 1 , wherein said resin is selected from the group consisting of a UV-curable resin and a heat-curable resin.
11. The gas turbine engine of claim 1 , wherein said flame retardant material is coated with a ceramic selected from the group consisting of alumina, mullite, and zirconia.
12. A gas turbine engine, comprising:
a gas turbine engine component having at least a portion of an exterior surface covered by at least one flame prevention device; and
said gas turbine engine component comprising at least one of a bleed tube disposed external to the engine casing and connecting a compressor section to a combustion section and an elbow joint connecting an end of said bleed tube to said engine casing;
said at least one flame prevention device comprising at least two pieces of flame retardant material sealed together; and
said at least two pieces comprising at least two pieces of a flame retardant ceramic foam.
13. The gas turbine engine of claim 12 , wherein said at least two pieces of flame retardant material are sealed together using any one of the following: mechanical fasteners, coatings and adhesives.
14. The gas turbine engine of claim 12 , wherein said at least one flame prevention device has a thickness of about 5 mils (127 μm) to about 2000 mils (5.08×10 4 μm).