Angled honeycomb seal between turbine rotors and turbine stators in a turbine engine
A seal system for an intersection between a turbine stator and a turbine rotor to seal cooling fluids. The seal system may be formed from a seal base extending from the turbine stator, an arm extending radially outward from the turbine rotor and toward the seal base but terminating short of the seal base thereby creating a gap between the seal base and the arm. The seal system may include a honeycomb shaped seal attached to the seal base and extending radially inward from the seal base toward the arm. An outer sealing surface of the seal may be nonparallel with a longitudinal axis about which the turbine rotor rotates thereby enabling the distance of the gap to be reduced with axial movement of the turbine rotor.
1 . A seal system for an intersection between a turbine stator and a turbine rotor, comprising:
a seal base extending from the turbine stator;
an arm extending from the turbine rotor and toward the seal base, but terminating short of the seal base thereby creating a gap between the seal base and the arm;
a seal attached to the seal base and extending radially inward from the seal base toward the arm, wherein an outer sealing surface of the seal is nonparallel with a longitudinal axis about which the turbine rotor rotates thereby enabling the distance of the gap to be reduced with axial movement of the turbine rotor.
2 . The seal system of claim 1 , wherein the outer sealing surface of the seal faces generally radially inward toward the arm and includes a first edge proximate to the turbine rotor and a second edge axially removed from the turbine rotor, wherein the second edge is positioned more radially inward than the first edge, thereby creating an angled sealing surface angled towards the turbine rotor such that as the turbine rotor is moved axially toward the turbine stator, the gap between the turbine rotor and turbine stator is reduced.
3 . The seal system of claim 1 , wherein the outer sealing surface of the seal faces generally radially inward toward the arm and includes a first edge proximate to the turbine rotor and a second edge axially removed from the turbine rotor, wherein the first edge is positioned more radially inward than the second edge, thereby creating an angled sealing surface angled away from the turbine rotor such that as the turbine rotor is moved axially away from the turbine stator, the gap between the turbine rotor and turbine stator is reduced.
4 . The seal system of claim 1 , wherein the arm extends radially outward from the turbine rotor.
5 . The seal system of claim 1 , wherein the seal is formed from a honeycomb shaped material.
6 . A seal system for an intersection between a turbine stator and a turbine rotor, comprising:
a seal base extending from the turbine stator;
an arm extending radially outward from the turbine rotor and toward the seal base, but terminating short of the seal base thereby creating a gap between the seal base and the arm;
a honeycomb shaped seal attached to the seal base and extending radially inward from the seal base toward the arm, wherein an outer sealing surface of the seal is nonparallel with a longitudinal axis about which the turbine rotor rotates thereby enabling the distance of the gap to be reduced with axial movement of the turbine rotor.
7 . The seal system of claim 6 , wherein the outer sealing surface of the seal faces generally radially inward toward the arm and includes a first edge proximate to the turbine rotor and a second edge axially removed from the turbine rotor, wherein the second edge is positioned more radially inward than the first edge, thereby creating an angled sealing surface angled towards the turbine rotor such that as the turbine rotor is moved axially toward the turbine stator, the gap between the turbine rotor and turbine stator is reduced.
8 . The seal system of claim 6 , wherein the outer sealing surface of the seal faces generally radially inward toward the arm and includes a first edge proximate to the turbine rotor and a second edge axially removed from the turbine rotor, wherein the first edge is positioned more radially inward than the second edge, thereby creating an angled sealing surface angled away from the turbine rotor such that as the turbine rotor is moved axially away from the turbine stator, the gap between the turbine rotor and turbine stator is reduced.
9 . A seal system for an intersection between turbine components, comprising:
a seal base extending from a first turbine component;
an arm extending radially outward from the first turbine component and toward a second turbine component, but terminating short of the seal base thereby creating a gap between the seal base and the arm;
a honeycomb shaped seal attached to the seal base and extending radially inward from the seal base toward the arm, wherein an outer sealing surface of the seal is nonparallel with a sealing surface of the arm thereby enabling the distance of the gap to be reduced with axial movement of the second turbine component.
10 . The seal system of claim 9 , wherein the outer sealing surface of the seal faces generally radially inward toward the arm and includes a first edge proximate to the second turbine component and a second edge axially removed from the second turbine component, wherein the second edge is positioned more radially inward than the first edge, thereby creating an angled sealing surface angled towards the second turbine component such that as the second turbine component is moved axially toward the first turbine component, the gap between the second turbine component and the first turbine component is reduced.
11 . The seal system of claim 9 , wherein the outer sealing surface of the seal faces generally radially inward toward the arm and includes a first edge proximate to the second turbine component and a second edge axially removed from the second turbine component, wherein the first edge is positioned more radially inward than the second edge, thereby creating an angled sealing surface angled away from the second turbine component such that as the second turbine component is moved axially away from the first turbine component, the gap between the second turbine component and the first turbine component is reduced.
12 . The seal system of claim 9 , wherein the first turbine component is a turbine rotor and the second turbine components is a turbine stator.