Turbine engine with a blade assembly having a dovetail

A dovetail assembly for a turbine engine, the dovetail assembly comprising:

• a platform including a stator rotor seal having a seal upper surface and a seal end surface, with a seal junction defined where the seal upper surface meets the seal end surface;
• and
• a dovetail extending from the platform, wherein the dovetail comprises:
• an aft face;
• an inlet passage extending through the dovetail and defining a passage axis, wherein the inlet passage is positioned such that the passage axis is spaced from the aft face by a spacing distance of 0.275 in;
• a first portion including a first upper lobe, a first lower lobe, and a first intervening recess between the first upper lobe and the first lower lobe;
• a first curved surface partially defining the first lower lobe and the first intervening recess;
• a first planar surface partially defining the first lower lobe and the first intervening recess;
• a second portion including a second upper lobe, a second lower lobe, and a second intervening recess between the second upper lobe and second lower lobe, with the second upper lobe having a second lobe upper surface;
• and
• a pressure face surface defining a planar potion of the second lobe upper surface;
• wherein a spaced plane is defined parallel to the aft face and parallel to and intersecting the passage axis, the spaced plane spaced from the aft face by the spacing distance;
• wherein an offset plane is defined offset from the spaced plane by 10-degrees rotated about the passage axis;
• wherein a first radius length (L) is defined as a radius of curvature of the first curved surface measured along the offset plane, and wherein the first radius length (L) is between 0.04 in and 0.105 in;
• wherein a first length (LPF) is defined as a length defined by the first planar surface measured along the offset plane, and wherein the first length (LPF) is between 0.071 in and 0.080 in;
• wherein a second width (CVX) is defined as a minimum length between the passage axis and a furthest extent of a gage pin from the inlet passage when the gage pin is provided within the second intervening recess, wherein the gage pin is a 0.165 in gage pin, wherein the second width (CVX) is measured along the offset plane, and wherein the second width (CVX) is between 0.315 in and 0.335 in;
• wherein a recess width (CVMN) is defined as a minimum length between the inlet passage and the second intervening recess measured along the offset plane, and wherein the recess width (CVMN) is between 0.050 in and 0.140 in;
• wherein a pressure face area (UPF) is defined as an area of the pressure face surface, wherein the pressure face area (UPF) is between 0.195 in2 and 0.230 in2;
• and
• wherein a seal radius (R) is defined as a radius of curvature of the seal junction, wherein the seal radius (R) is between 12.410 in (31.521 cm) and 12.460 in (31.6484 cm);
• wherein the first length (LPF), the second width (CVX), the pressure face area (UPF), and the seal radius (R) define a first value (EQ1) by the following expression:
• E
• ⁢
• Q
• ⁢
• 1
• =
• (
• LPF
• 0.075
• in
• )
• 4
• *
• (
• CVX
• 0.31
• in
• )
• 1
• 4
• *
• (
• (
• UPF
• 0.19
• in
• 2
• )
• (
• R
• 8.88
• in
• )
• )
• 1
• 4
• ;
• wherein the first radius length (L), the recess width (CVMN), the pressure face area (UPF), and the seal radius (R) define a second value (EQ2) by the following expression:
• E
• ⁢
• Q
• ⁢
• 2
• =
• (
• L
• 0.08
• in
• )
• 6
• *
• (
• CVMN
• 0.08
• in
• )
• 1
• 6
• *
• (
• (
• UPF
• 0.19
• in
• 2
• )
• (
• R
• 8.88
• in
• )
• )
• 1
• 3
• ;
• and
• wherein the first value (EQ1) is between 0.7457 and 1.2418 and the second value (EQ2) is between 0.0138 and 5.3494.