Integral compressor housing of gas turbine engines

A compressor module for a gas engine, comprising:

• an external housing having:
• a forward end and an aft end,
• an open mode inlet duct and a closed mode inlet duct in said external housing,
• a forward bearing housing conically extending from said forward end of said external housing into said external housing,
• a bell mouth circumferentially disposed within said external housing,
• a forward flange on said forward end, and
• an aft flange on said aft end;
• a compressor wheel rotatably disposed at said aft end on a shaft;
• and
• a compressor shroud/diffuser disposed circumferentially about said compressor wheel;
• wherein said bell mouth and said compressor wheel provide an air path for air to flow to said rotatable compressor wheel and to be discharged into a compressor discharge scroll at an increased pressure from a pressure at said inlet duct.

A compressor module for a gas turbine engine of an aircraft, comprising:

• an external housing having:
• a forward end and an aft end,
• an open mode inlet duct and a closed mode inlet duct in said external housing,
• a forward bearing housing conically extending from said forward end of said external housing and into said external housing,
• a bell mouth circumferentially disposed within said external housing,
• a forward flange on said forward end, and
• an aft flange on said aft end;
• a compressor wheel rotatably disposed at said aft end on a shaft;
• a compressor shroud/diffuser disposed circumferentially about said compressor wheel, wherein said bell mouth and said compressor wheel provide an air path for air to flow to said rotatable compressor wheel and to be discharged into a compressor discharge scroll at an increased pressure from a pressure at said inlet duct;
• a hole in an apex portion of said conically extending forward bearing housing, wherein said shaft extends from said compressor wheel through said hole;
• a forward bearing disposed within said forward bearing housing, said forward bearing providing axial and radial support of said shaft extending through said hole of said forward bearing housing;
• a speed sensor for measuring the speed of rotation of said shaft;
• a speed sensor boss to isolate potential oil leakage from the flow path;
• a generator housing attached to said single aft flange;
• and
• a generator within said generator housing, said generator converting rotational energy of said shaft into electrical energy.

A gas turbine engine comprising:

• a compressor module having:
• an external housing with a forward end and an aft end,
• an open mode inlet duct and a closed mode inlet duct in said external housing,
• a forward bearing housing conically extending from said forward end of said external housing and into said external housing,
• a bell mouth circumferentially disposed within said external housing,
• a forward flange on said forward end, and
• an aft flange on said aft end;
• a combustion section attached at said aft end of said external housing;
• a generator housing attached at said forward end of said external housing;
• and
• a generator within said generator housing.

A gas turbine engine used as an auxiliary power unit for an aircraft, comprising:

• a compressor module having:
• an external housing with a forward end and an aft end,
• an open mode inlet duct and a closed mode inlet duct in said external housing,
• a forward bearing housing conically extending from said forward end of said external housing and into said external housing,
• a bell mouth circumferentially disposed within said external housing,
• a forward flange on said forward end, and
• an aft flange on said aft end;
• a combustion section attached at said aft end of said external housing;
• a generator housing attached at said forward end of said external housing;
• a generator within said generator housing;
• a shaft extending from said combustion section, through said compressor module, and into said generator housing;
• a compressor wheel rotatably disposed at said aft end on said shaft;
• a hole in an apex portion of said conically extending forward bearing housing, wherein said shaft extends from said compressor wheel through said hole;
• a forward bearing disposed within said forward bearing housing, said forward bearing providing axial and radial support of said shaft;
• and
• a speed sensor for measuring the speed of rotation of said shaft;
• wherein said bell mouth and said compressor wheel provide an air path for air to flow to said rotatable compressor wheel and to be discharged into a compressor discharge scroll at an increased pressure from a pressure at said inlet duct.

A method of providing auxiliary power with a gas turbine engine:

• providing a compressor module having an external housing with a forward end and an aft end, an open mode inlet duct and a closed mode inlet duct in said external housing, a forward bearing housing conically extending from said forward end of said external housing into said external housing, and a bell mouth circumferentially disposed within said external housing;
• attaching a generator housing at said forward end of said external housing;
• providing a generator within said generator housing;
• attaching a combustion section attached at said aft end of said external housing;
• extending a shaft from said combustion section, through said compressor module and into said generator housing;
• rotatably disposing a compressor wheel at said aft end on said shaft;
• rotating said shaft to provide mechanical rotational power to said generator;
• and
• converting said mechanical rotational power to electrical power.