Jet engine variable area turbine nozzle

In a gas turbine engine subassembly having an axial turbine including a longitudinally forward-most row of rotor blades, a turbine nozzle comprising:

• (a) a generally annular inner casing extending generally longitudinally forward and aft;
• (b) a generally annular outer casing spaced apart from and generally coaxially surrounding said inner casing;
• (c) first and second circumferentially adjacent turbine nozzle vanes each fixedly attached to at least one of said inner and outer casings, said vanes disposable longitudinally adjacent and forward of said blades, said vanes each having a generally airfoil shape with a leading edge, a suction side, a trailing edge, and a pressure side, and said pressure side of said first vane circumferentially spaced apart from said suction side of said second vane defining a vane airflow passage bounded by said vanes and said inner and outer casings;
• (d) a plug member having a portion insertable into and withdrawable from said vane airflow passage through one of said inner and outer casings proximate at least said pressure side of said first vane;
• and
• (e) means for inserting said portion into and withdrawing said portion from said vane airflow passage, and also including a generally longitudinally extending axis, wherein said outer casing has a region having a generally constant slope towards said axis as one moves longitudinally aft of said trailing edge of said first vane, wherein said portion of said plug member has a longitudinally forward edge and a longitudinally aft edge each generally aligned with said slope, and wherein said inserting and withdrawing means inserts and withdraws said portion of said plug member proximately along said region.