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A rotor assembly for a gas turbine engine, the rotor assembly comprises at least two rotors defining a cavity therebetween. A first rotor defines a cooling air inlet in its radially inward portion. A second rotor defines a cooling air outlet in its radially outward portion, such that the cooling air

A rotor assembly for a gas turbine engine, the rotor assembly comprises at least two rotors defining a cavity therebetween. A first rotor defines a cooling air inlet in its radially inward portion. A second rotor defines a cooling air outlet in its radially outward portion, such that the cooling air passes radially outwardly through the cavity.

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We claim: 1. A rotor assembly for a gas turbine engine, the rotor assembly comprising: first and second rotors defining a first cavity therebetween, wherein each rotor comprises a disc carrying an annular array of radially extending blades; the first rotor defining a cooling air inlet in a radially

We claim: 1. A rotor assembly for a gas turbine engine, the rotor assembly comprising: first and second rotors defining a first cavity therebetween, wherein each rotor comprises a disc carrying an annular array of radially extending blades; the first rotor defining a cooling air inlet in a radially inward portion of the first rotor; the second rotor defining a cooling air outlet in a radially outward portion of the second rotor, such that cooling air passes radially outwardly through said first cavity during operation of the engine; a third rotor having a bore and defining a second cavity with said second rotor, wherein during operation of the engine said cooling air passes through said outlet then passing into and radially inwardly through said second cavity to pass through said bore; and a fourth rotor defining a third cavity with the third rotor, during operation of the engine the cooling air that passes through the bore of the third rotor then passes into and radially outwardly through the third cavity to pass through a second cooling air outlet defined in a radially outward portion of the fourth rotor, the fourth rotor having a second bore sealed by a seal so that cooling air cannot flow through the second bore, wherein the seal comprises a small clearance between the bore of the rotor and a shaft such that the airflow into the respective cavity preferentially passes through the cooling air outlet. 2. A rotor assembly for a gas turbine engine, said rotor assembly comprising: first and second rotors defining a first cavity therebetween, the first rotor having a first bore and the second rotor having a second bore, wherein each rotor comprises a disc carrying an annular array of radially extending blades; a shroud having a cooling air inlet for flowing cooling air into the first cavity during operation of the engine so that the cooling air flows radially inward through the first cavity and flows through the first and second bores; a third rotor defining a second cavity with the second rotor, the third rotor having a first air outlet at a radially outward portion of the third rotor, and the third rotor having a third bore that is sealed with a seal to prevent cooling air from flowing through the third bore, such that during operation of the engine cooling air flows from the second bore into the second cavity and flows in a radially outward direction through the second cavity and into the first air outlet; and a fourth rotor defining a third cavity with the first rotor, the fourth rotor having a second air outlet at a radially outward portion of the fourth rotor, and the fourth rotor having a fourth bore that is sealed with a seal to prevent cooling air from flowing through the fourth bore, such that during operation of the engine cooling air flows from the first bore into the third cavity and flows in a radially outward direction through the third cavity and into the second air outlet, wherein the seal comprises a small clearance between the bore of the rotor and a shaft such that the airflow into the respective cavity preferentially passes through the cooling air outlet. 3. A rotor assembly as claimed in claim 1, wherein the cooling air passes in a generally rearward direction through the rotor assembly during operation of the engine. 4. A rotor assembly as claimed in claim 2, wherein during operation of the engine the cooling air traveling from the first cavity to the second cavity travels in a rearward direction and the cooling air traveling from the first cavity to the third cavity travels in a forward direction. 5. A rotor assembly as claimed in claim 1, wherein said cooling air outlet is angled in the axial direction. 6. A rotor assembly as claimed in claim 1, wherein the cooling air outlet is angled tangentially such that the cooling air has a component of velocity in the tangential direction. 7. A rotor assembly as claimed in claim 6, wherein the cooling air outlet is angled tangentially in the direction of rotation of the disc. 8. A rotor assembly as claimed in claim 6, wherein the cooling air outlet is angled tangentially in the opposite direction of rotation of the disc. 9. A rotor assembly as claimed in claim 1, wherein the cooling air outlet is angled radially such that the cooling air has a component of velocity in the radial direction. 10. A rotor assembly as claimed in claim 9, wherein the cooling air outlet is angled radially inwardly or radially outwardly. 11. A rotor assembly as claimed in claim 1, wherein the cooling air inlet is a bore of the first rotor. 12. A rotor assembly as claimed in claim 1, wherein a shaft passes through the bore of at least some of the rotors of the rotor assembly. 13. A rotor assembly as claimed in claim 1, wherein the seal is a labyrinth seal. 14. A rotor assembly as claimed in claim 1 wherein the assembly is a compressor assembly. 15. A rotor assembly as claimed in claim 1 wherein the assembly is a turbine assembly. 16. A gas turbine engine comprising a rotor assembly as claimed in claim 1. 17. A rotor assembly according to claim 2, wherein the seal is a labyrinth seal.