A method of depositing an abradable coating on a gas turbine engine component, comprising: (a) forming a slurry mixture comprising at least bi-modal ceramic particulate with up to 70% by volume of coarse particulate, the coarse particles have an average size ranging from 2 micrometers to 10 micrometers, wherein said coarse particulate is at least one of Ln2Si2O7, Ln2SiO5, silica, barium strontium aluminosilicate (BSAS), monoclinic hafnium oxide, rare earth gallium garnet (Ln2Ga2O9) where Ln is at least one of Scandium (Sc), Yttrium, Lanthanum (La), Cerium (Ce), Praseodymium (Pr), Neodymium (Nd), Samarium (Sm), Europium (Eu), Gadolinium (Gd), Terbium (Tb), Dysprosium (Dy), Holmium (Ho), Erbium (Er), Thulium (Tm), Ytterbium (Yb), Lutetium (Lu), and up to 60 % by volume of fine particulate, the fine particles have an average particle size equal to or less than 2 micrometers, wherein said fine particulate includes at least one of Ln2Si2O7 or Ln2SiO5 where Ln is at least one of Sc, Y, La, Ce, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, a dispersant for said ceramic particulate, and a monomer solution, a free-radical initiator compound, a low vapor pressure organic solvent and at least one sinter aid selected from the group consisting of consisting of iron, aluminum, titanium, cobalt, nickel, gallium, tin, indium, any compounds thereof (e.g. oxides, acetates, oxalates, carbides, nitrides, carbonates, acetylacetonates, nitrates, silicides, any compounds containing a rare earth element, etc), mixtures thereof, or mixtures of compounds thereof; (b) applying said slurry mixture to at least one of said gas turbine engine component and a mold; (c) gelling said slurry mixture to polymerize and crosslink forming a firm irreversible gel matrix on said gas turbine component with said monomer solution and said free-radical initiator compound by heating said mold containing at least one of said gas turbine engine component and said slurry mixture to a first temperature between 30° C - 80° C before evaporation of said organic solvent; (d) drying said irreversible gel matrix at a second temperature of between 80° C to 250° C; and, (e) sintering said particulate of said dried irreversible gel matrix on said gas turbine engine component at a temperature greater than 1204° C and less than 1357° C forming a layer of said coating having a thickness greater than 152 micrometers (6 mils) and a porosity of 5 percent to 50 percent, wherein said sintered layer comprises a doped rare earth disilicate where the sintering aid is a doping composition that dissolves into, and dopes the rare earth disilicate. (a) forming a slurry mixture comprising at least bi-modal ceramic particulate with up to 70% by volume of coarse particulate, the coarse particles have an average size ranging from 2 micrometers to 10 micrometers, wherein said coarse particulate is at least one of Ln2Si2O7, Ln2SiO5, silica, barium strontium aluminosilicate (BSAS), monoclinic hafnium oxide, rare earth gallium garnet (Ln2Ga2O9) where Ln is at least one of Scandium (Sc), Yttrium, Lanthanum (La), Cerium (Ce), Praseodymium (Pr), Neodymium (Nd), Samarium (Sm), Europium (Eu), Gadolinium (Gd), Terbium (Tb), Dysprosium (Dy), Holmium (Ho), Erbium (Er), Thulium (Tm), Ytterbium (Yb), Lutetium (Lu), and up to 60 % by volume of fine particulate, the fine particles have an average particle size equal to or less than 2 micrometers, wherein said fine particulate includes at least one of Ln2Si2O7 or Ln2SiO5 where Ln is at least one of Sc, Y, La, Ce, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, a dispersant for said ceramic particulate, and a monomer solution, a free-radical initiator compound, a low vapor pressure organic solvent and at least one sinter aid selected from the group consisting of consisting of iron, aluminum, titanium, cobalt, nickel, gallium, tin, indium, any compounds thereof (e.g. oxides, acetates, oxalates, carbides, nitrides, carbonates, acetylacetonates, nitrates, silicides, any compounds containing a rare earth element, etc), mixtures thereof, or mixtures of compounds thereof; (b) applying said slurry mixture to at least one of said gas turbine engine component and a mold; (c) gelling said slurry mixture to polymerize and crosslink forming a firm irreversible gel matrix on said gas turbine component with said monomer solution and said free-radical initiator compound by heating said mold containing at least one of said gas turbine engine component and said slurry mixture to a first temperature between 30° C - 80° C before evaporation of said organic solvent; (d) drying said irreversible gel matrix at a second temperature of between 80° C to 250° C; and, (e) sintering said particulate of said dried irreversible gel matrix on said gas turbine engine component at a temperature greater than 1204° C and less than 1357° C forming a layer of said coating having a thickness greater than 152 micrometers (6 mils) and a porosity of 5 percent to 50 percent, wherein said sintered layer comprises a doped rare earth disilicate where the sintering aid is a doping composition that dissolves into, and dopes the rare earth disilicate.