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 100 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), Phraseodymium (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 65 % 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 polymer solution consisting essentially of one anionic and one cationic dispersant such that the slurry becomes a reversible gel, a low vapor pressure organic solvent and at least one sinter aid selected from the group consisting of iron, aluminum, titanium, cobalt, nickel, gallium, indium, any compounds thereof (e.g. oxides, acetates, oxalates, carbides, nitrides, carbonates, acetylacetonates, nitrates, silicides, compounds containing a rare earth element), mixtures thereof, or mixtures of compounds thereof; (b) direct writing said reversible gel slurry to said gas turbine engine component; (c) drying said reversible gel slurry at one of room temperature or a second temperature between 30° C - 80° C to form a reversible gel matrix; and, (d) sintering said dried reversible gel matrix on said gas turbine engine component at a temperature greater than about 1204° C and less than 1357° C, forming a layer of said abradable coating having a thickness greater than 127 micrometers (5 mils) and a porosity of about 5 percent to about 50 percent, wherein said sintered layer is also comprised of a doped rare earth disilicate where said at least one 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 100 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), Phraseodymium (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 65 % 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 polymer solution consisting essentially of one anionic and one cationic dispersant such that the slurry becomes a reversible gel, a low vapor pressure organic solvent and at least one sinter aid selected from the group consisting of iron, aluminum, titanium, cobalt, nickel, gallium, indium, any compounds thereof (e.g. oxides, acetates, oxalates, carbides, nitrides, carbonates, acetylacetonates, nitrates, silicides, compounds containing a rare earth element), mixtures thereof, or mixtures of compounds thereof; (b) direct writing said reversible gel slurry to said gas turbine engine component; (c) drying said reversible gel slurry at one of room temperature or a second temperature between 30° C - 80° C to form a reversible gel matrix; and, (d) sintering said dried reversible gel matrix on said gas turbine engine component at a temperature greater than about 1204° C and less than 1357° C, forming a layer of said abradable coating having a thickness greater than 127 micrometers (5 mils) and a porosity of about 5 percent to about 50 percent, wherein said sintered layer is also comprised of a doped rare earth disilicate where said at least one sintering aid is a doping composition that dissolves into, and dopes the rare earth disilicate.