A turbomachine, comprising: a turbomachine blade, comprising: a tip shroud , including a nose portion , the nose portion including a leading edge overhang , wherein the leading edge overhang has a leading edge , the nose portion being downstream of the leading edge , and an intermediate portion downstream of the nose portion , wherein the leading edge and the nose portion are directly adjacent to one another, and the nose portion and the intermediate portion are directly adjacent to one another; and a stationary structural component disposed about the turbomachine blade, and comprising a corresponding portion corresponding to the leading edge portion of the tip shroud, wherein the corresponding portion has a first corresponding portion , a second corresponding portion downstream of the first corresponding portion, and a third corresponding portion downstream of the second corresponding portion, wherein the leading edge of the leading edge overhang and the first corresponding portion have substantially parallel contours that are substantially perpendicular to an axis of rotation of the turbomachine, the nose portion and the second corresponding portion have substantially parallel contours that are substantially parallel to the axis of rotation of the turbomachine, the intermediate portion and the third corresponding portion have substantially parallel contours that are disposed at an acute angle relative to the axis of rotation of the turbomachine, and the first corresponding portion and the second corresponding portion are continuous and directly adjacent to one another, and the second corresponding portion and the third corresponding portion are continuous and directly adjacent to one another, wherein the leading edge , the nose portion and the intermediate portion are directly exposed across a clearance to the first corresponding portion , the second corresponding portion and the third corresponding portion respectively. a tip shroud , including a nose portion , the nose portion including a leading edge overhang , wherein the leading edge overhang has a leading edge , the nose portion being downstream of the leading edge , and an intermediate portion downstream of the nose portion , wherein the leading edge and the nose portion are directly adjacent to one another, and the nose portion and the intermediate portion are directly adjacent to one another; and a stationary structural component disposed about the turbomachine blade, and comprising a corresponding portion corresponding to the leading edge portion of the tip shroud, wherein the corresponding portion has a first corresponding portion , a second corresponding portion downstream of the first corresponding portion, and a third corresponding portion downstream of the second corresponding portion, wherein the leading edge of the leading edge overhang and the first corresponding portion have substantially parallel contours that are substantially perpendicular to an axis of rotation of the turbomachine, the nose portion and the second corresponding portion have substantially parallel contours that are substantially parallel to the axis of rotation of the turbomachine, the intermediate portion and the third corresponding portion have substantially parallel contours that are disposed at an acute angle relative to the axis of rotation of the turbomachine, and the first corresponding portion and the second corresponding portion are continuous and directly adjacent to one another, and the second corresponding portion and the third corresponding portion are continuous and directly adjacent to one another, wherein the leading edge , the nose portion and the intermediate portion are directly exposed across a clearance to the first corresponding portion , the second corresponding portion and the third corresponding portion respectively. <EOS>